![Page 1: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/1.jpg)
ACTIVITY SHEETAIRFOIL
FLUENT SIMULATIONAE4015 COMPUTATIONAL AERODYNAMICS
EMA AMALIA, ST., MT.
![Page 2: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/2.jpg)
SIMULATION OF AIRFOIL NACA 65(2)-415
![Page 3: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/3.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• TO DO SIMULATION ON AIRFOIL NACA 65(2)-415, HERE WE WILL USE ICEM CFD TO
CONSTRUCT GEOMETRY
• AIRFOIL THAT HAS BEEN CONSTRUCTED USING SPACECLAIM IS FOR CONSTRUCTING WING. IT
WON’T BE GOOD FOR AIRFOIL CFD SIMULATION
![Page 4: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/4.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• NOW WE WILL CONTINUE, FIRST, WE DOWNLOAD THE AIRFOIL COORDINATE FROM “UIUC
AIRFOIL DATA SITE” UNDER THE ALPHABET “N” (HTTPS://M-
SELIG.AE.ILLINOIS.EDU/ADS/COORD_DATABASE.HTML#N) AND CHOOSE “NACA652415.DAT”
![Page 5: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/5.jpg)
![Page 6: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/6.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• OPEN THE FILE “NACA652415.DAT” IN MS EXCEL, ADD AN ADDITIONAL COLUMN FOR Z VALUE OF 0 (BECAUSE
WE WORK IN 2 DIMENSIONAL).
• ADD SOME INFO AT THE TOP OF FILE AS IN THE NEXT SLIDE
• REMEMBER THAT THE SEQUENCE OF AIRFOIL COORDINATE DATA SHOULD CONSIST OF TWO CURVES:
1. FROM LEADING EDGE TO TRAILING EDGE THROUGH UPPER SURFACE
2. FROM LEADING EDGE TO TRAILING EDGE THROUGH LOWER SURFACE
• REMEMBER TO ADJUST THE NUMBER OF POINTS TO MATCH WITH THE NUMBER OF COORDINATE
DATA POINTS. FOR EXAMPLE, IF YOU WRITE DOWN THE DATA NUMBER IS 26, YOU SHOULD MODIFY
THE COORDINATE DATA POINTS TO BE 26 TOO.
![Page 7: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/7.jpg)
Original
Data
From
NACA652415.DAT
Number of point
in each curve
Number of curves
Change sequence of upper surface
to be from LE to TE
Adding a point of 0,0,0 to upper
surface so that the number of point
will be 26 for each curves
Additional column of z
![Page 8: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/8.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• COPY THE MODIFIED DATA OF AIRFOIL COORDINATE TO A NEW SHEET, AND SAVE IN FORMAT
“TEXT (TAB DELIMITED)” AS *.DAT”, FOR EXAMPLE “NACA652415PROFILE.DAT”. BECAUSE EXCEL
HAS NO FORMAT OF “*.DAT”, JUST ENTER “NACA652415PROFILE.DAT” AS INPUT TO FILE NAME
• NOW, THE *.DAT FILE IS READY TO BE IMPORTED FROM ICEM CFD
![Page 9: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/9.jpg)
![Page 10: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/10.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• LAUNCH ICEM CFD:
1. FROM WORKBENCH: DRAG “ICEM CFD” FROM LEFT WINDOW TO MAIN WINDOW AND
RIGHT CLICK “MODEL”, CHOOSE “EDIT”. THEN ICEM CFD WILL BE LAUNCHED. OR DOUBLE CLICK
“MODEL”, AND ICEM CFD WILL BE LAUNCHED.
![Page 11: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/11.jpg)
![Page 12: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/12.jpg)
![Page 13: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/13.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• OR LAUNCH ICEM CFD STANDALONE
![Page 14: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/14.jpg)
![Page 15: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/15.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• THE DIFFERENCE BETWEEN ICEM CFD LAUNCHED FROM WORKBENCH AND STANDALONE
Launched from Workbench
Launched Standalone
![Page 16: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/16.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• IF YOU WORK WITH WORKBENCH, DON’T FORGET TO “SAVE PROJECT” FROM FILE TAB (DO
NOT USE UPDATE PROJECT), EXIT TO WORKBENCH, AND SAVE YOUR WORKBENCH PROJECT IN
DIFFERENT NAMES FOR SOME STEPS, IN CASE YOU DO A WRONG STEP, YOU DON’T NEED TO
REPEAT FROM ZERO.
![Page 17: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/17.jpg)
![Page 18: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/18.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• IF YOU WORK WITH ICEM CFD STANDALONE, DON’T FORGET TO “SAVE PROJECT AS”
FREQUENTLY WITH DIFFERENT NAMES FOR SOME STEPS, SO THAT IF YOU DO A WRONG STEP,
YOU DON’T NEED TO START FROM ZERO.
(YOU CAN DO THIS FROM “FILE” TAB, AND CHOOSE “SAVE PROJECT AS”, THEN WRITE DOWN
THE NAME OF INTERMEDIATE FILE, FOR EXAMPLE: “NACA652415 STEP 1. PRJ”
![Page 19: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/19.jpg)
![Page 20: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/20.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• IN THIS ACTIVITY SHEET, THE GUIDELINES WILL BE MAINLY DONE FROM WORKBENCH. BUT IF
YOU WORK FROM STANDALONE ICEM CFD, IT WILL BE VERY SIMILAR.
![Page 21: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/21.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• FROM ICEM CFD, CHOOSE FILE => IMPORT GEOMETRY => FORMATTED POINT DATA. SELECT
THE *.DAT FILE “ (FOR EXAMPLE: NACA652415PROFILE.DAT)
![Page 22: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/22.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• THEN CLICK APPLY IN LOWER-LEFT WINDOW
![Page 23: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/23.jpg)
![Page 24: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/24.jpg)
PREPARING GEOMETRY OF THE AIRFOIL
• IF WE CHECK “POINTS” IN STRUCTURE TREE, THEN POINTS OF AIRFOIL COORDINATE WILL
APPEAR
![Page 25: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/25.jpg)
![Page 26: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/26.jpg)
PREPARING GEOMETRY OF THE AIRFOIL• RENAME THE PARTS. FOR EXAMPLE: CRVS BECOMES AIRFOIL BY RIGHT CLICK THE PARTS
• DELETE UNNECESSARY PARTS, FOR EXAMPLE “SURFS”
![Page 27: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/27.jpg)
MAKING COMPUTATIONAL DOMAIN
• NOW WE WILL MAKE COMPUTATIONAL DOMAIN
• WE WILL CREATE SOME POINTS AS FOLLOWS:
(-20,0,0); (0,20,0); (0,-20,0); (21,20,0), (21,-20,0)
![Page 28: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/28.jpg)
MAKING COMPUTATIONAL DOMAIN• FROM GEOMETRY TAB, CHOOSE “CREATE POINT”, CHOOSE “XYZ” OPTION TO INPUT COORDINATES
Uncheck
XYZ option
Enter coordinates
of points
![Page 29: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/29.jpg)
MAKING COMPUTATIONAL DOMAIN• REPEAT TO DRAW POINTS OF OUTER BOUNDARIES OF COMPUTATIONAL DOMAIN
(-20,0,0)
(0,20,0)
(0,-20,0)
(21,20,0)
(21,-20,0)
![Page 30: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/30.jpg)
MAKING COMPUTATIONAL DOMAIN
• CREATE CURVE FROM GEOMETRY TAB, CONNECT THE OUTER BOUNDARIES OF
COMPUTATIONAL DOMAIN
Uncheck
Choose this option
for straight liines
Click to select a point, middle click to confirm,
Repeat for all straight lines
![Page 31: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/31.jpg)
![Page 32: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/32.jpg)
MAKING COMPUTATIONAL DOMAIN• CREATE CURVE FROM GEOMETRY TAB, CONNECT THE OUTER BOUNDARIES OF
COMPUTATIONAL DOMAIN
Uncheck
Choose this option
for half circle
Click to select three points that construct semi-circle
Boundary, middle click to confirm
![Page 33: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/33.jpg)
![Page 34: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/34.jpg)
MAKING COMPUTATIONAL DOMAIN• WE WILL MAKE SURFACE OF COMPUTATIONAL DOMAIN
• CLICK “CREATE SURFACE” IN GEOMETRY TAB, AND CHOOSE “SIMPLE SURFACE” SELECT CURVES
OF OUTER BOUNDARIES BY CLICKS AND MIDDLE CLICKS TO CONFIRM
Enter the name of part as “Fluid”
Uncheck
Choose this simple surface option
![Page 35: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/35.jpg)
![Page 36: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/36.jpg)
CREATE BLOCKING• CHOOSE BLOCKING TAB, CLICK CREATE BLOCK
• CHOOSE PART OF “FLUID” AS BLOCKING, AND SELECT “2D PLANAR”, CLICK APPLY
![Page 37: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/37.jpg)
![Page 38: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/38.jpg)
CREATE BLOCKING• STILL IN BLOCKING TAB, CLICK ASSOCIATE AND “ASSOCIATE EDGE TO CURVE”
• CHOOSE EDGE OF BACK BOUNDARY TO ASSOCIATE WITH BACK CURVE WITH CLICK AND
MIDDLE-CLICK UNTIL THE EDGES BECOME GREEN.
• CHOOSE EDGE OF UPPER, FRONT, AND
LOWER BOUNDARIES TO ASSOCIATE WITH UPPER, SEMI-CIRCLE, AND LOWER CURVES WITH
CLICK AND MIDDLE-CLICK UNTIL THE EDGES BECOME GREEN.
![Page 39: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/39.jpg)
![Page 40: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/40.jpg)
CREATE BLOCKING• STILL IN BLOCKING TAB, CLICK ASSOCIATE MENU, CHOOSE “SNAP PROJECT VERTICES”
![Page 41: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/41.jpg)
![Page 42: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/42.jpg)
MODIFY BLOCKING
• MODIFY EXISTING BLOCKING BY EDIT EDGE AND SPLIT EDGE
• SELECT METHOD SPLINE TO EDIT EDGE IN NEAR SEMI-CIRCLE CURVE SO
THAT THE EDGE WILL FOLLOW THE CURVE’S SHAPE.
![Page 43: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/43.jpg)
![Page 44: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/44.jpg)
MODIFY BLOCKING
• AND SELECT METHOD LINEAR TO GRADUALLY CHANGE THE SHAPE OF THE REST EDGE TO
FOLLOW THE CURVES. NOW THE SHAPE OF THE BLOCKING IS THE SAME WITH THE DOMAIN.
![Page 45: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/45.jpg)
![Page 46: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/46.jpg)
MODIFY THE BLOCK• STILL IN BLOCKING MENU, CHOOSE SPLIT BLOCK AND CHOOSE OGRID BLOCK
• SELECT BLOCK BY CLICKING AREA INSIDE OUTER BOUNDARIES, AND SELECT EDGE OF OUTLET
![Page 47: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/47.jpg)
![Page 48: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/48.jpg)
CLICK APPLY
![Page 49: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/49.jpg)
MODIFY THE BLOCK• USE MOVE VERTEX AND CLICK IN LOWER-LEFT WINDOW, THEN MOVE VERTICES SO
THAT THE POSITIONS WILL BE AS IN THE NEXT TWO FIGURE
Select vertices by click
And drag with mouse
To their new places
![Page 50: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/50.jpg)
this vertex
this vertex
this vertex
this vertex
![Page 51: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/51.jpg)
Vertices in their new positions
![Page 52: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/52.jpg)
MODIFY BLOCK
• STILL IN BLOCKING TAB, SELECT SPLIT BLOCK AND CLICK SPLIT BLOCK
![Page 53: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/53.jpg)
MODIFY BLOCK
• SELECT EDGE BEHIND AIRFOIL (THE RED EDGE) BY CLICK, DRAG THE MOUSE TO POSITION OF SPLIT
![Page 54: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/54.jpg)
![Page 55: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/55.jpg)
MODIFY BLOCK
• STILL FROM BLOCKING MENU, SELECT MERGE VERTICES AND COLLAPSE BLOCK ,
![Page 56: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/56.jpg)
MODIFY BLOCK
• ACTIVATE BLOCKS
This edge This block to
collapse
• Click the edge, click block to collapse, middle click
![Page 57: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/57.jpg)
![Page 58: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/58.jpg)
MODIFY THE BLOCK• USE MOVE VERTEX AND CLICK IN LOWER-LEFT WINDOW, THEN MOVE VERTICES SO
THAT THE POSITIONS WILL BE AS IN THE NEXT TWO FIGURE
Select vertices by click
And drag with mouse
To their new places
![Page 59: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/59.jpg)
This vertex
![Page 60: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/60.jpg)
Become at this position
![Page 61: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/61.jpg)
MODIFY BLOCK• STILL FROM BLOCKING TAB, CHOOSE ASSOCIATE , AND ASSOCIATE VERTEX TO POINT
![Page 62: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/62.jpg)
Select this vertex
![Page 63: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/63.jpg)
Click this point
So that the vertex turned to red
![Page 64: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/64.jpg)
MODIFY BLOCK
• STILL FROM BLOCKING TAB, CHOOSE ASSOCIATE , AND ASSOCIATE VERTEX TO POINT
![Page 65: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/65.jpg)
MODIFY BLOCK
• ASSOCIATE TWO VERTICES TO TWO POINTS AS FOLLOWS
This point
This point
This vertex
This vertex
![Page 66: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/66.jpg)
Vertex turned into red
Vertex turned into red
![Page 67: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/67.jpg)
MODIFY BLOCK• STILL IN BLOCKING TAB, CLICK ASSOCIATE AND “ASSOCIATE EDGE TO CURVE”
Check “project
vertices”
![Page 68: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/68.jpg)
Click this edges to associate with
Airfoil curves, then middle click
![Page 69: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/69.jpg)
Click these two
curves, middle click
![Page 70: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/70.jpg)
![Page 71: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/71.jpg)
MODIFY BLOCKING
• MODIFY EXISTING BLOCKING BY EDIT EDGE AND SPLIT EDGE
• SELECT METHOD LINEAR TO EDIT EDGES INSIDE AIRFOIL TO FOLLOW
AIRFOIL CURVE
![Page 72: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/72.jpg)
Make these edges follow
The airfoil curve
By split edge
With linear method
![Page 73: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/73.jpg)
![Page 74: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/74.jpg)
MODIFY BLOCK
• STILL IN BLOCKING TAB, CHOOSE SPLIT BLOCK , AND CLICK SPLIT BLOCK AND
SELECT THE EDGE (THE RED ONE) BY CLICK SO THAT THERE WILL BE AN ADDITIONAL BLOCK
AROUND AIRFOIL. THEN MIDDLE CLICK TO CONFIRM.
![Page 75: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/75.jpg)
![Page 76: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/76.jpg)
Additional block
Near airfoil
![Page 77: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/77.jpg)
MODIFY BLOCK
• WE WILL DELETE BLOCK INSIDE THE AIRFOIL BY CHOOSING DELETE BLOCK
• CLICK THE BLOCK INSIDE AIRFOIL, MIDDLE CLICK TO CONFIRM TO DELETE.
![Page 78: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/78.jpg)
We will delete this block
![Page 79: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/79.jpg)
• THERE IS NO MORE BLOCK INSIDE THE AIRFOIL
![Page 80: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/80.jpg)
• CHECK BLOCKS IN UPPER LEFT WINDOW TO VIEW BLOCKS IN OUR COMPUTATIONAL DOMAIN
![Page 81: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/81.jpg)
PREPARING FOR MESHING
• IF YOU WORK WITH WORKBENCH, SAVE THE WORKBENCH WITH DIFFERENT NAME BEFORE YOU
DO MESHING
• IF YOU WORK WITH STANDALONE ICEM CFD, SAVE THE PROJECT WITH DIFFERENT NAME BEFORE
YOU DO MESHING
THIS STEP ENSURE YOU TO HAVE A FILE OF GEOMETRY WITH COMPLETE BLOCKING BEFORE MESHING,
SO THAT IF YOU MAKE A MISTAKE IN MESHING YOU CAN GO BACK AND RESTART FROM THIS FILE.
![Page 82: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/82.jpg)
• FOR EXAMPLE, HERE WE SAVE WORKBENCH PROJECT WITH COMPLETE BLOCKING
![Page 83: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/83.jpg)
NOW WE ARE READY FOR MESHING
![Page 84: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/84.jpg)
• FOR EXAMPLE, WE SAVE AN INTERMEDIATE WORKBENCH PROJECT AS FOLLOWS
• YOU CAN DO THE SIMILAR IF YOU WORK WITH STANDALONE ICEM CFD
![Page 85: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/85.jpg)
MESHING• CALCULATING ESTIMATED WALL DISTANCE BY Y+ = 1 (HTTPS://WWW.CFD-
ONLINE.COM/TOOLS/YPLUS.PHP) => CHORD IS 1.O (TO BE ADJUSTED TO 1.625 LATER)
The estimated wall distance
![Page 86: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/86.jpg)
MESHING
• OPEN YOUR AIRFOIL GEOMETRY COMPLETE WITH BLOCKING IN ICEM CFD EITHER FROM
WORKBENCH OR FROM ICEM CFD STANDALONE
![Page 87: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/87.jpg)
![Page 88: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/88.jpg)
• UNCHECK BLOCKS
![Page 89: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/89.jpg)
MESHING
• STILL IN BLOCKING TAB, CHOOSE PRE-MESH PARAM AND EDGE PARAMS
• SELECT EDGE AS IN NEXT SLIDE (RED ONE)
• SET PARAMETER IN LOWER-LEFT WINDOW AS FOLLOWS
This from y+=1
Scroll
![Page 90: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/90.jpg)
![Page 91: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/91.jpg)
MESHING
• SET COPY TO PARAMETERS => ALL PARALLEL EDGES
• CLICK APPLY
![Page 92: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/92.jpg)
![Page 93: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/93.jpg)
• RECOMPUTE PRE-MESH BY RIGHT CLICK ON THE TREE OF “PRE-MESH”
![Page 94: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/94.jpg)
![Page 95: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/95.jpg)
MESHING• WE STILL SEE THAT THE PRE-MESH IS PENETRATING THE AIRFOIL SURFACE
• FROM BLOCKING TAB, CLICK (“GRID PARAMS”) AND CLICK (“UPDATE SIZES”), APPLY
![Page 96: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/96.jpg)
Now, we get pre-mesh that not penetrating airfoil
![Page 97: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/97.jpg)
MESHING
• REPEAT THE PREVIOUS PROCEDURE TO SET MESH AT THE EDGE
• STILL IN BLOCKING TAB, CHOOSE PRE-MESH PARAM AND EDGE PARAMS
• SELECT EDGE AS IN NEXT SLIDE (RED ONE)
• SET PARAMETER IN LOWER-LEFT WINDOW AS FOLLOWS
Scroll This from y+=1
![Page 98: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/98.jpg)
Set copy to parameters => All Parallel Edges
Click apply
![Page 99: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/99.jpg)
• RECOMPUTE PRE-MESH, ACTIVATE PRE-MESH
![Page 100: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/100.jpg)
MESHING
• WE WILL SET MESH FOR OTHER NECESSARY EDGES
![Page 101: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/101.jpg)
MESHING
• STILL IN BLOCKING TAB, CHOOSE PRE-MESH PARAM AND EDGE PARAMS
• SELECT EDGE BEHIND THE AIRFOIL (RED ONE WITH ARROWS)
• SET NODES FOR EXAMPLE 1500
• SET MESH LAW AS “BIGEOMETRIC”
• LET OTHER VALUES AS GIVEN BY SOFTWARE
• SET COPY PARAMETER => ALL PARALLEL EDGES
![Page 102: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/102.jpg)
![Page 103: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/103.jpg)
• CLICK APPLY AND RECOMPUTE PRE-MESH AND ACTIVATE IT
![Page 104: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/104.jpg)
MESHING
• STILL IN BLOCKING TAB, CHOOSE PRE-MESH PARAM AND EDGE PARAMS
• SELECT EDGES OF SURFACE OF AIRFOIL (RED ONE WITH ARROWS)
• SET NODES FOR EXAMPLE 400
• SET MESH LAW AS “BIGEOMETRIC”
• LET OTHER VALUES AS GIVEN BY SOFTWARE
• SET COPY PARAMETER => ALL PARALLEL EDGES
![Page 105: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/105.jpg)
![Page 106: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/106.jpg)
• CLICK APPLY, RECOMPUTE PRE-MESH AND ACTIVATE IT
![Page 107: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/107.jpg)
MESHING
• STILL IN BLOCKING TAB, CHOOSE PRE-MESH PARAM AND EDGE PARAMS
• SELECT EDGE IN FRONT OF LEADING EDGE OF AIRFOIL(RED ONE WITH ARROWS)
• SET NODES FOR EXAMPLE 50
• SET MESH LAW AS “BIGEOMETRIC”
• LET OTHER VALUES AS GIVEN BY SOFTWARE
• SET COPY PARAMETER => ALL PARALLEL EDGES
![Page 108: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/108.jpg)
![Page 109: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/109.jpg)
• CLICK APPLY, RECOMPUTE PRE-MESH AND ACTIVATE IT
![Page 110: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/110.jpg)
MESHING
• STILL IN BLOCKING TAB, CHOOSE PRE-MESH PARAM AND EDGE PARAMS
• SELECT EDGE NEAR FARFIELD (RED ONE WITH ARROWS)
• SET NODES FOR EXAMPLE 600
• SET MESH LAW AS “BIGEOMETRIC”
• LET OTHER VALUES AS GIVEN BY SOFTWARE
• SET COPY PARAMETER => ALL PARALLEL EDGES
![Page 111: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/111.jpg)
![Page 112: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/112.jpg)
• CLICK APPLY, RECOMPUTE PRE-MESH AND ACTIVATE IT
![Page 113: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/113.jpg)
MESHING
• RIGHT CLICK ON PRE-MESH, AND CHOOSE “CONVERT TO UNSTRUCT MESH”
• IF THERE IS A WINDOW THAT “MESH ALREADY EXISTS”, CLICK “REPLACE”
![Page 114: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/114.jpg)
• NOW WE HAVE ALREADY HAD A MESH
![Page 115: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/115.jpg)
NOW WE ARE READY FOR SIMULATION
![Page 116: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/116.jpg)
SET SOLVER
• CHOOSE OUTPUT MESH TAB AND CHOOSE SELECT SOLVER
• CHOOSE ANSYS FLUENT
![Page 117: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/117.jpg)
SET BOUNDARY CONDITIONS• FROM OUTPUT MESH TAB, CHOOSE (“BOUNDARY CONDITIONS”)
• FIRST, SET BOUNDARY CONDITION FOR “AIRFOIL” THAT APPEARS IN “EDGES”
• FOLLOW STEPS IN THE NEXT SLIDE
![Page 118: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/118.jpg)
1. Click “create new”
2. Choose “wall”
3. Click “Okay”
![Page 119: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/119.jpg)
SET BOUNDARY CONDITIONS
• THEN SET BOUNDARY CONDITION OF FARFIELD
• FROM “?MIXED/UNKNOWN” , CHOOSE FARFIELD
• FOLLOW STEPS IN THE NEXT SLIDE
![Page 120: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/120.jpg)
1. Click “create new”
2. Choose “velocity inlet”
3. Click “okay”
![Page 121: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/121.jpg)
SET BOUNDARY CONDITIONS
• SET THE BOUNDARY CONDITION OF FLUID
• FROM “? MIXED/UNKNOWN”, CHOOSE “FLUID”
• FOLLOW STEPS IN THE NEXT SLIDE
![Page 122: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/122.jpg)
1. Click “create new”
2. Choose “fluid”
3. Click “Okay”
![Page 123: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/123.jpg)
SET BOUNDARY CONDITIONS
• THEN WE WILL HAVE COMPLETE BOUNDARY CONDITIONS
• CLICK ACCEPT
![Page 124: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/124.jpg)
WRITE OUTPUT FILE• FROM OUTPUT MESH TAB, CHOOSE (“WRITE OUTPUT”)
![Page 125: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/125.jpg)
WRITE OUTPUT FILE
• CLICK OPEN FOR DEFAULT *.UNS FILE WHEN ASKED
![Page 126: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/126.jpg)
WRITE OUTPUT FILE
• BECAUSE WE WILL OPEN FLUENT MESH BY FLUENT STANDALONE, NAME MESH WITH A UNIQUE
NAME.
• MAKE SURE THE CASE IS “2D”
![Page 127: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/127.jpg)
Remember this working directory and the name of mesh file
![Page 128: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/128.jpg)
PREPARING FOR SIMULATION IN FLUENT
• SAVE YOUR PROJECT AND CLOSE YOUR WORKBENCH OR STANDALONE ICEM CFD
• LAUNCH STANDALONE FLUENT IN 2D CASE WITH DOUBLE PRECISION OPTION
• CLICK “OK”
![Page 129: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/129.jpg)
SIMULATION IN FLUENT
![Page 130: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/130.jpg)
SIMULATION IN FLUENT
• CHOOSE FILE => READ => MESH
![Page 131: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/131.jpg)
SIMULATION IN FLUENT
• CHOOSE THE MESH FILE
THAT WE SAVED
PREVIOUSLY
• CLICK OK
![Page 132: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/132.jpg)
• MESH DISPLAYED IN FLUENT
![Page 133: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/133.jpg)
SIMULATION IN FLUENT
• FIRST, WE WILL SCALE THE GEOMETRY AND MESH OF AIRFOIL TO HAVE A CHORD LENGTH OF
1.625.
• FROM GENERAL SETUP, CLICK “SCALE”
![Page 134: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/134.jpg)
SIMULATION IN FLUENT• IN SCALING MENU, CHOOSE “SPECIFY SCALING FACTOR”
• ENTER FACTORS OF 1.625 FOR BOTH X AND Y, CLICK “SCALE” UNTIL THE VALUES ARE
CHANGED
![Page 135: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/135.jpg)
SIMULATION IN FLUENT
• AFTER SCALING, AGAIN IN GENERAL SETUP, WE MAKE SURE THAT THE SETUP IS AS BELOW
![Page 136: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/136.jpg)
SIMULATION IN FLUENT
• IN MODELS SETUP, CLICK “VISCOUS” AND CHOOSE “SPALART ALMARAS”
• CLICK OK
![Page 137: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/137.jpg)
![Page 138: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/138.jpg)
SIMULATION IN FLUENT
• IN MATERIALS SETUP, CHOOSE UNDER “FLUID”: “AIR” UNTIL A POP WINDOW APPEARS
• MAKE SURE THAT WE CHOOSE AIR AT SEA LEVEL CONDITION AS IN THE NEXT SLIDE
• CLICK CHANGE/CREATE AND CLICK CLOSE
![Page 139: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/139.jpg)
![Page 140: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/140.jpg)
SIMULATION IN FLUENT• IN CELL-ZONE CONDITIONS, CLICK “FLUID”, AND CLICK “OPERATING CONDITIONS”
![Page 141: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/141.jpg)
SIMULATION IN FLUENT• ENTER 1 ATM OR 101325 PA FOR A POSITION OF FARFIELD IN THE FRONT. HERE WE USE THE
POINT OF (-32.5,0)
![Page 142: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/142.jpg)
SIMULATION IN FLUENT
• WE CHECK BOUNDARY CONDITIONS
• AIRFOIL IS WALL
![Page 143: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/143.jpg)
SIMULATION IN FLUENT
• FARFIELD IS VELOCITY INLET
• CLICK “EDIT”
![Page 144: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/144.jpg)
SIMULATION IN FLUENT• SET VELOCITY AS “COMPONENT” AND ENTER THE VALUE OF FREESTREAM VELOCITY OF 26.82
M/S
![Page 145: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/145.jpg)
SIMULATION IN FLUENT
• INT_FLUID AS “INTERIOR”
![Page 146: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/146.jpg)
SIMULATION IN FLUENT
• SET REFERENCE VALUES AS FOLLOWS
![Page 147: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/147.jpg)
SIMULATION IN FLUENT• IN MONITORS, WE WILL MAKE ADDITIONAL MONITORS OF CL, CD, AND CM. CLICK “REPORT
PLOTS” AND CLICK “NEW”
![Page 148: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/148.jpg)
SIMULATION IN FLUENT• CREATE DRAG MONITORS
![Page 149: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/149.jpg)
SIMULATION IN FLUENT
• DRAG REPORT DEFINITION
![Page 150: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/150.jpg)
SIMULATION IN FLUENT
• CREATE LIFT MONITORS
![Page 151: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/151.jpg)
SIMULATION IN FLUENT
• LIFT REPORT DEFINITIONS
![Page 152: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/152.jpg)
SIMULATION IN FLUENT
• CREATE MOMENT MONITORS
![Page 153: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/153.jpg)
SIMULATION IN FLUENT
• MOMENT REPORTS DEFINITION0.25chord
![Page 154: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/154.jpg)
SIMULATION IN FLUENT
• IN SOLUTION INITIALIZATION, CHOOSE “STANDARD INITIALIZATION” AND COMPUTE FROM
“FARFIELD” AND LET OTHER VALUES AUTOMATICALLY DETERMINED BY SOFTWARE
• CLICK “INITIALIZE”
![Page 155: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/155.jpg)
Click “Initialize”
![Page 156: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/156.jpg)
SIMULATION IN FLUENT
• NOW, WE ARE READY TO RUN CALCULATION.
• ENTER ITERATION OF 500, WHICH COULD BE REPEATED LATER IF NOT CONVERGENT.
• BECAUSE NOT SET, THE CONVERGENCE CRITERIA WILL BE BY DEFAULT 1E-4.
• CLICK “CALCULATE” TO START SIMULATION IN FLUENT
![Page 157: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/157.jpg)
![Page 158: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/158.jpg)
![Page 159: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/159.jpg)
SIMULATION IN FLUENT
• SIMULATION WILL TAKE ABOUT 8800 - 9800 ITERATIONS FOR ABOUT 7-16 HOURS
SIMULATION TO CONVERGED (AT I7 OR I5 PROCESSOR).
• YOU CAN’T DO ITERATION FOR EACH 1000 ITERATIONS AND SAVE THE CASE & DATA FOR
EACH 1000 ITERATIONS AND CONTINUE (DO NOT INITIALIZE, JUST CLICK CALCULATE)
• DON’T FORGET TO SAVE THE WORK FROM FILE => WRITE => CASE & DATA
• THE RESULT WILL BE EVALUATED BY EXPERIMENTAL RESULT AFTER POST-PROCESSING
![Page 160: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/160.jpg)
![Page 161: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/161.jpg)
NOW WE ARE READY FOR POST-PROCESSING
![Page 162: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/162.jpg)
DISPLAYING LIFT COEFFICIENT
• WE WILL DISPLAY THE RESULT OF LIFT. CLICK “REPORTS”, CLICK “FORCES”, CLICK “SET UP” AND
A POP-UP WINDOW APPEARS
• THEN SET “DIRECTION VECTOR” OF Y AS 1 BECAUSE FOR ANGLE OF ATTACK 0 DEGREE, THE
LIFT FORCE IS IN Y POSITIVE DIRECTION.
![Page 163: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/163.jpg)
![Page 164: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/164.jpg)
• CLICK “PRINT” AND A LIFT COEFFICIENT VALUE WILL APPEAR IN LOWER-RIGHT WINDOW
![Page 165: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/165.jpg)
DISPLAYING DRAG COEFFICIENT
• WE WILL DISPLAY THE RESULT OF DRAG. CLICK “REPORTS”, CLICK “FORCES”, CLICK “SET UP”
AND A POP-UP WINDOW APPEARS
• THEN SET “DIRECTION VECTOR” OF X AS 1 BECAUSE FOR ANGLE OF ATTACK 0 DEGREE, THE
DRAG FORCE IS IN X POSITIVE DIRECTION.
![Page 166: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/166.jpg)
![Page 167: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/167.jpg)
• CLICK “PRINT” AND YOU WILL SEE THE DRAG COEFFICIENT VALUE IN LOWER-RIGHT WINDOW
![Page 168: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/168.jpg)
WRITING THE LIFT AND DRAG COEFFICIENT TO FILE• YOU CAN SAVE THE LIFT OR DRAG COEFFICIENT TO FILE BY CLICK “WRITE” INSTEAD OF “PRINT”
THEN INPUT THE FILE NAME
![Page 169: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/169.jpg)
COMPARING WITH EXPERIMENTAL DATA
• IT IS IMPORTANT TO COMPARE OUR RESULT OF CFD SIMULATION WITH ANOTHER DATA TO
KNOW THE QUALITY OF RESULT. HERE WE WILL COMPARE WITH EXPERIMENTAL DATA OF
AIRFOIL NACA 65(2)-415 TAKEN FROM NACA REPORT. THE FILE OF NACA REPORT WILL BE
PROVIDED.
![Page 170: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/170.jpg)
From experimental at 0 degree with Reynolds number 3e6, lift coefficient is 0.3 and drag coefficient is 0.007
![Page 171: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/171.jpg)
COMPARING WITH EXPERIMENTAL DATA
• FROM EXPERIMENTAL DATA, AT 0 DEGREE WITH REYNOLDS NUMBER OF 3 MILLIONS, LIFT
COEFFICIENT IS 0.3 AND DRAG COEFFICIENT IS 0.007 (CL/CD (AERODYNAMICS EFFICIENCY) IS
ABOUT 42)
• THE RESULT OF CFD SIMULATION, THE LIFT COEFFICIENT IS 0.548 AND DRAG COEFFICIENT IS
0.0128 (CL/CD (AERODYNAMICS EFFICIENCY) IS ABOUT 42)
• WE CAN SEE THAT THE CFD SIMULATION IS IN MEDIUM QUALITY, BECAUSE IT HAS THE SAME
ORDER WITH EXPERIMENTAL RESULT, BUT IF YOU WILL USE CFD SIMULATION RESULT FOR A
PROJECT, YOU SHOULD MODIFY THE MESHING OR CHANGE TURBULENCE MODEL USED.
![Page 172: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/172.jpg)
DISPLAYING ABSOLUTE PRESSURE CONTOUR
• IT IS IMPORTANT TOO TO CHECK WHETHER THE TOTAL PRESSURE CONTOUR IS AS IT SHOULD
BE, WHICH IS 1 ATM AT FARFIELD.
• CLICK “GRAPHICS”, CLICK “CONTOURS”, CLICK “SET UP” UNTIL A POP-UP WINDOW APPEARS.
• CHOOSE “PRESSURE” AND “ABSOLUTE PRESSURE”
• CHOOSE “INT_FLUID” OF SURFACE
• CLICK “COMPUTE”, WAIT, AND CLICK “SAVE/DISPLAY”.
• USE “FIT TO WINDOW” TO SEE THE WHOLE DOMAIN.
![Page 173: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/173.jpg)
![Page 174: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/174.jpg)
The CFD simulation results in correct values of 1 atm (about 1.01325e5 Pa) at farfield
![Page 175: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/175.jpg)
SHOWING STATIC PRESSURE CONTOURS• WE WILL CHECK STATIC PRESSURE CONTOURS AROUND THE AIRFOIL WHETHER IT HAVE A
NEGATIVE STATIC PRESSURE ON THE UPPER SURFACE AS IT SHOULD BE.
• CLICK “GRAPHICS”, CLICK “CONTOURS”, CLICK “SET UP” UNTIL A POP WINDOW APPEARS.
• CHOOSE “PRESSURE” AND “STATIC PRESSURE”
• CHOOSE “INT_FLUID” OF SURFACE
• CLICK “COMPUTE”, WAIT, AND CLICK “SAVE/DISPLAY”. CHOOSE THE WINDOW TO VIEW THE
STATIC PRESSURE CONTOUR.
• USE “ZOOM TO AREA” TO SEE CONTOUR NEAR THE AIRFOIL.
![Page 176: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/176.jpg)
![Page 177: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/177.jpg)
![Page 178: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/178.jpg)
SAVING CONTOUR PLOT
• IF YOU NEED TO SAVE THE CONTOUR PLOT, CHOOSE “SAVE PICTURE” FROM THE ICON.
• THEN A POP UP WINDOW WILL APPEAR, ENTER THE THE FILE TYPE.
• CLICK “SAVE”, AND ENTER THE FILE NAME.
![Page 179: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/179.jpg)
![Page 180: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/180.jpg)
EXAMPLE OF JPEG PICTURE OF STATIC PRESSURE CONTOUR
![Page 181: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/181.jpg)
EVALUATION OF STATIC PRESSURE CONTOUR
• WE SEE FROM STATIC PRESSURE CONTOUR THAT THERE IS A NEGATIVE STATIC PRESSURE AREA
ON UPPER SURFACE OF AIRFOIL, THIS FACT CONFIRM THAT THE CFD SIMULATION IS CORRECT
ACCORDING TO THEORY.
![Page 182: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/182.jpg)
DISPLAYING VELOCITY CONTOUR
• WE WILL CHECK THAT AT FARFIELD, THE VELOCITY SHOULD BE 26.82 M/S.
• CLICK “GRAPHICS”, CLICK “CONTOURS”, CLICK “SET UP” UNTIL A POP WINDOW APPEARS.
• CHOOSE “VELOCITY”, CHOOSE “VELOCITY MAGNITUDE”
• CLICK “COMPUTE”, WAIT, CLICK “SAVE/DISPLAY”
• SELECT THE WINDOW TO SHOW THE CONTOUR OF VELOCITY
• SELECT “FIT TO WINDOW” TO SEE WHOLE OF DOMAIN
![Page 183: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/183.jpg)
![Page 184: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/184.jpg)
We see that the velocity near of farfield is of correct value of 26.82 m/s
26.82
![Page 185: Activity sheet airfoil and wing fluent simulation](https://reader031.vdocuments.mx/reader031/viewer/2022021710/620b2cc8ef717d08c426fa17/html5/thumbnails/185.jpg)
NOTE ON POST-PROCESSING
• THERE IS MANY THINGS CAN BE DISPLAYED IN POST-PROCESSING, YOU CAN TRY BY YOURSELF
• FOR EXAMPLE, DISPLAYING VELOCITY VECTORS NEAR AIRFOIL SURFACE, AND CHECKING
VELOCITY PROFILE OF BOUNDARY LAYER.