copy of raymer simplified aircraft design spreadsheet (sam)

Simplified Aircraft Design Spreadsheet for HomebuildersVersion 1.0 Copyright C 2003 by Daniel P. Raymer. All Rights Reserved. See legal notice for further restrictions.

LEGAL NOTICE ! Better to save this spreadsheet as a renamed copy before changing it for your airplane, in case it gets messed up!

Inputs Calculated ValuesStall speed (kts) 8 Stall speed (ft/sec) 13.5Takeoff air density (slugs/ft^3) 0.00238 Dynamic pressure (psf) 0.2Wing CLmax 1 Wing loading (W/S) (psf) 0.22

power loading (lb/hp) 0.14

Engine Power (hp -each) 1.65 Wo (lb) 0.2Number of Engines 1 Wing Area (sq ft) 1.1

Swet/Sref 4.2Cfe 0.0053 Cdo 0.0223Aspect ratio (A) 6.3 K (=1/piAe) 0.0674Cruise air density (slugs/ft^3) 0.00176 W/S cruise 0.2Cruise velocity (kts) 24 Cruise velocity (ft/sec) 40.5

Dynamic pressure (psf) 1.4L/D cruise 6.21

Engine SFC 0.45 Engine SFC 0.000125Prop Efficiency (cruise) 0.75Range (nmi) 800 Range (ft) 4860800

Breguet Exponent 0.2373Wf/Wo 0.2310

Fuel allowance (%) 6 Wf/Wo with allow. 0.2448Empty Weight constant "a" 11.86Weight - crew (lbs) 0Weight - Passengers (lbs) 0Weight - payload (lbs) 0 See Sizing Graph sheet for Wo Results

Wing taper ratio 0 Wing Span (ft) 2.59Root Chord (ft) 0.82Tip Chord (ft) 0.00Mean Chord (ft) 0.55

Horizontal tail arm (ft) 10 Tail areas:Cht (volume coeff) 0.6 Sht (horizontal) (sq ft) 0.03Vertical tail arm (ft) 10Cvt (volume coeff) 0.04 Svt (vertical) (sq ft) 0.01

Shar

e -

war

e !

Win

g Lo

adin

gW

o -k

now

n en

gine

If sizing to a range requirement, ignore this input for now but enter it later when Wo is calculated and engine is selected

You cannot enter Wo! Engine power and power loading are multiplied to calculate Wo. If sizing to a range requirement, do calculation below, read Wo from graph, and select an engine that gives the desired Wo=P*P/W

Wo

Sizi

ng to

a ra

nge

requ

irem

ent (

engi

ne is

no

t yet

sel

ecte

d)

(lb/hour /bhp)

(lb/sec /bhp)

Win

g G

eom

etry

Tail

Sizi

ng

B4

THIS SPREADSHEET IS NOT FREEWARE! It is provided free of charge ONLY to original purchasers of the book Dan Raymer's Simplified Aircraft Design for Homebuilders. Others wanting to use it LEGALLY must send $25 to: Design Dimension Press PO Box 5429 Playa del ReySylmar, CA 90296, USA (CA residents add $2 for sales taxes) For information about school licenses please contact the author at [email protected]. This spreadsheet may NOT be modified or edited (other than to input data for your airplane), nor incorporated in any other spreadsheet or program, without the written permission of the author. LICENSE AGREEMENT AND DISCLAIMER OF WARRANTY: This Simplified Aircraft Design spreadsheet is COPYRIGHT (C) 2003 by DANIEL P. RAYMER. ALL RIGHTS RESERVED. No part of this spreadsheet software may be reproduced, distributed, or transmitted, in any form or by any means, or stored in a database retrieval system, without prior written permission of Daniel P. Raymer. This license agreement replaces and supersedes any and all other agreements, explicit or implied, concerning this product, including any terms and conditions attached to or included with the payment for this product, unless such terms have been agreed to in writing, signed by the Copyright holder. 1. Design Dimension Press and Daniel P. Raymer ("the purveyors") provide this spreadsheet software for use "as-is" and without any expressed or implied warranty as to accuracy or fitness for any use. The purveyors do not warrant or guarantee the use, or the results of the use, of the software in terms of correctness, accuracy, reliability, currentness, merchantability, or fitness for any purpose, and assume no responsibility for errors, omissions, or damage, including without limitation damages caused by the use of this computer program or from the use of information contained therein. The entire risk and performance of the software is assumed by the user. In no event shall Design Dimension Press, Daniel P. Raymer, or anyone else involved in the creation, production, distribution, and support of this software be liable for direct, indirect, special, or consequential damages, nor for any costs or expenses associated with implementing the software to perform any specific purpose, nor for claims by you based upon third-party claims. Design Dimension Press warrants the spreadsheet software program only to be free of material defects that would prevent loading the software on the user's computer system and running the program. NO OTHER WARRANTY, REPRESENTATION, OR CONDITION IS EXPRESSED OR IMPLIED. 2. This software is licensed SOLELY for use in aircraft conceptual design, and may not be used for final design or analysis of existing, modified, or new actual aircraft, including but not limited to the prediction of aerodynamic, weight, propulsion, stability, cost, range, and performance characteristics. No data produced by this software may be used for prediction of flight characteristics of actual aircraft, and this software may not be used to produce flight handbooks or any other information to be used for flight of actual aircraft. Purchaser assumes the liability for the unauthorized use of software results as described above by third parties to whom the purchaser has provided such results. 3. The original purchaser may make backup copies of the software as needed, which may not be sold, rented, lent, or in any other way transferred to another person or organization. 4. Please note that if this software is licensed for use by or on behalf of a unit or agency of the United States Government, this license agreement still applies in full. This spreadsheet software was developed without government funds at private expense and in all respects is proprietary data copyrighted solely to Daniel P. Raymer. 5. This spreadsheet software was developed for use with Microsoft Excel™ and cannot be run without it. Purchase of a license for this spreadsheet software does not include a copy of Excel™ and the user is responsible for purchase and installation of Excel™. (Design Dimension Press is a subsidiary of Conceptual Research Corporation and the terms should be considered synonymous in the statements above)

F12

If you really want to use a particular engine, and you really want a particular Wo, you must cheat! Calculate power loading (W/hp) from these values and enter it and the horsepower of your engine. This should give you the Wo you want. However, you should check the performance calculations because the results may not be what you want!

B17

including landing gear drag if not retractable

Simplified Aircraft Design Spreadsheet for HomebuildersVersion 1.0 Copyright C 2003 by Daniel P. Raymer. All Rights Reserved. See legal notice for further restrictions.

Better to save this spreadsheet as a renamed copy before changing it for your airplane, in case it gets messed up! Send problems & questions to [email protected]

Other Factors Used Equations (from book) Misc Useful Calcs

e (Oswald) 0.75Wcruise/Wo 0.98

CL-cruise 0.1472

Non-cruise weight allowance 0.975

Empty Weight exponent -0.09 Fuel Weight 0.1 (lbs)Fuel Vol 0.0 (gal)

Enter items in blue and purple. Come back and re-enter purple items after the drawing is analyzed.

(OK to change these if you know what you are doing)

Preliminary tail sizing using these methods does not guarantee that the aircraft will be stable, controllable, or safe. You must perform stability calculations after doing your design layout!

LD

=1

qCD 0

W /S+(W /S ) K

q

q= 12ρV

Stall2

WS

=qC L

CD0=C fe

Swet

Sref

K=1

0 .75 π A=0 .424A

W f /W 0=1−0 .975 e

−R c bhp500 ηp L /D

W 0=W people+W payload

1−W E /W 0−W F /W 0

W E /W 0=aW0−0 . 09

B2

Based on the methods, definitions, and equations in Dan Raymer's Simplified Aircraft Design for Homebuilders, Design Dimension Press, Los Angeles, 2003. For ordering information please visit http://www.aircraftdesign.com

B3

THIS SPREADSHEET IS NOT FREEWARE! See legal notice in red box.

Send problems & questions to [email protected]

Sizing Calculations

Wo guess We/Wo We Wo calculated1000 6.3692 6369.2 0.01500 6.1410 9211.4 0.02000 5.9840 11968.0 0.02500 5.8650 14662.6 0.0

Enter Wo from graph (lbs) 2000Pick engine with horsepower of at least: 14286

Power of Selected Engine: 120Calculated Power Loading: 16.67

Pick Wo from graph, where the two lines cross. Enter this value below to find the minimum horsepower engine for your power loading.

If sizing graph lines do not cross, change Wo-guess values above.

Now find a suitable engine of at least this horsepower and enter its power below:

Now go to sheet 1 and enter the power of your selected engine and the power loading calculated above in the

boxes this color. 800 1000 1200 1400 1600 1800 2000 2200 2400 26000

500

1000

1500

2000

2500

3000Sizing Graph

Wo Guess

Wo

Cal

cula

ted

800 1000 1200 1400 1600 1800 2000 2200 2400 26000

500

1000

1500

2000

2500

3000Sizing Graph

Wo Guess

Wo

Cal

cula

ted

As-Drawn Performance Calculations for Simplified Aircraft Design for HomebuildersUse this sheet for performance calculations after you have drawn your design and measured its geometry.

Calculated ValuesWo (lb) 0 wing loading (W/S) (psf) 0.22Engine Power (hp) 2 stall speed (ft/sec) 13.51Number of Engines 1 stall speed (kts) 8.00Engine SFC (lb/hour /bhp) 0.45 power loading (lb/hp) 0.14Wing Area (sq ft) 1.1 Takeoff Parameter 0.0Cdo 0.0223 Takeoff Groundroll (ft) -49.7K (=1/piAe) 0.0674 Takeoff to 50 ft (ft) 50.3Wing CLmax 1Takeoff air density (slugs/ft^3) 0.00238e (Oswald) 0.75Wcruise/Wo 0.98 Cruise Weight (lb) 0.22638Non-cruise weight allowance 0.975Fuel allowance (%) 6Weight - crew (lbs) 0Weight - passengers (lbs) 0Weight - payload (lbs) 0Empty Weight (lbs) 3.1

Other InputsPropeller Diameter (ft) 5Engine RPM (rev/min) 2700Cooling Power Loss (%) 6Cruise Power Setting (% of SL hp) 62Cruise air density (slug/ft^3) 0.00176 Power Coefficient Cp 0.0018

Go to next sheet for climb, cruise, and maximum speed calculations then return here

Cruise speed (kts) 180 Cruise speed (ft/sec) 304.02Cruise Advance Ratio J 1.3512

Cruise Prop efficiency 0.85 Cruise q (psf) 81.3Cruise W/S (psf) 0.2Cruise L/D 0.1Wfuel (total) (lbs) -3Wfuel (usable) (lbs) -3Wfuel (cruise) (lbs) -3log term 0.0760378Range (ft) -1133175Range (nmi) -187

Values from Sheet 1 - OK to change these here, but then link from Sheet 1 is lost

F10

Uses straight-line approximation of takeoff parameter chart in book

B21

You should change this approximate empty weight value to match your group weight calculations. Or, you can change the empty weight constant "a" value on the first sheet so that this box produces the empty weight you calculated. This allows you to resize your design if you wish using a "calibrated" We/Wo equation.

B32

As found from chart on next sheet

As-Drawn Performance Calculations for Simplified Aircraft Design for HomebuildersUse this sheet for performance calculations after you have drawn your design and measured its geometry.

Equations (from book)

T .O .P .=1.21

WS

Whp

C Lmax

LD

=1

qCD 0

W /S+(W /S ) K

q

R=550 ηp

Cbhp

LDln [ 0 .975W 0

W 0−W f (usable ) ]

Climb, Cruise, & Max Speed Calculations for Simplified Aircraft Design for HomebuildersUse this sheet for performance calculations after you have drawn your design and measured its geometry.

V kts V ft/sec CL CD Drag lbs50 84.45 0.375333 0.59 5.959734 3.695035 6.2759862 0.034618 0.022341 0.149075

100 168.9 0.750667 0.8 4.040497 2.505108 25.1039448 0.008655 0.022265 0.59428150 253.35 1.126 0.85 2.862019 1.774452 56.4838758 0.003846 0.022261 1.336887200 337.8 1.501333 0.82 2.070755 1.283868 100.415779 0.002164 0.02226 2.376616220 371.58 1.651467 0.8 1.83659 1.138686 121.503093 0.001788 0.02226 2.875692

Input adjusted values

Advance Ratio J

Propeller Efficiency

Total Thrust lbs

Cruise Thrust lbs

Dynamic pressure q

Read Cruise speed where cruise thrust line crosses drag line and enter in cruise speed box (this color) on previous sheet

40 60 80 100 120 140 160 180 200 220 2400

200Maximum & Cruise Speed

Total ThrustCruise ThrustDrag

Velocity - kts

Thru

st o

r Dra

g -lb

s

40 60 80 100 120 140 160 180 200 220 2400

9500190002850038000475005700066500760008550095000

104500114000123500133000142500152000

Rate of Climb - Sea Level

Velocity - kts

Clim

b - f

pm

A5

If these velocities are too slow or too fast you can change them, but you must have only 5 velocities

D5

Using Power Coefficient from Sheet 3. Include adjustments for scrubbing drag and other propeller losses (see book).

H5

At takeoff weight Wo

Climb, Cruise, & Max Speed Calculations for Simplified Aircraft Design for HomebuildersUse this sheet for performance calculations after you have drawn your design and measured its geometry.

Equations (from book)

Climb (fps)130058.34154271.42102409.77-27384.02

-102335Read Cruise speed where cruise thrust line crosses drag line and enter in cruise speed box (this color) on previous

40 60 80 100 120 140 160 180 200 220 2400

9500190002850038000475005700066500760008550095000

104500114000123500133000142500152000

Rate of Climb - Sea Level

Velocity - kts

Clim

b - f

pm

D=qS(CD 0+KC L2)

CL−cruise=

WS

qq= 12ρV 2

Vv=V [ TW −1

L/D ]

Weight Reporting Format for Simplified Aircraft Design for HomebuildersUse this sheet for reporting weights calculations & estimating center of gravity. Input only items in blue

Weight Loc Moment Weight Loc Momentlbs ft ft-lbs lbs ft ft-lbs

STRUCTURES 661.0 5600 EQUIPMENT 69.0 429 Wing 276 6.5 1794 Flight Controls 10 5.5 55 Horizontal Tail 24 21.0 504 Instruments 10 5.5 55 Vertical Tail 18 19.0 342 Hydraulics 2 6.0 12 Ventral Tail 8 17.0 136 Electrical 12 6.0 72 Fuselage 155 9.0 1395 Avionics 15 5.0 75 Canopy 15 8.0 120 Air Conditioning 0 Nacelle on wing 50 9.0 450 Anti-Icing 0 Nacelle/cowling 30 7.5 225 Furnishings & Equipment 20 8.0 160 Motor Mount 10 7.5 75 Main Landing Gear 56 9.0 504 (% We Allowance) 10 enter % Nose Landing Gear 19 2.9 55 Empty Weight Allowance 114.1 7.8 891 don’t enter these

PROPULSION 411.0 2877 TOTAL WEIGHT EMPTY 1255.1 7.8 9797 Engine 340 7.0 2380 Air Induction 3 7.0 21 USEFUL LOAD 744.9 Cooling 3 7.0 21 Crew 0.0 8.0 0 Exhaust 8 7.0 56 Fuel 738.9 7.5 5542 Don't enter this! It is calculated from Wo, We, and other Useful Load Group items Engine Controls 2 7.0 14 Oil 6 5.0 30 Misc. Engine Inst 5 7.0 35 Passengers 0 8.0 0 Propeller 30 7.0 210 Payload 0 10.0 0 Starter 10 7.0 70 Fuel System 10 7.0 70 TAKEOFF GROSS WEIGHT 2000.0 7.7 15368

Crew+Pass+Pld, No Fuel 1261.1 7.8 9827Crew+Pass,No Pld,No Fuel 1261.1 7.8 9827Crew only, No Fuel 1261.1 7.8 9827Crew only, Full Fuel 2000.0 7.7 15368

(Sorry, no weights estimation methods here, just the form to enter your estimates. Moments & cg are calculated)

Calculated Empty Weight constant "a". Go to Initial Sizing Inputs sheet and revise value in purple box:

Pos

sibl

e Lo

adin

g C

ondi

tions

G22

From Sizing Inputs Sheet - OK to change but then link is lost

G25


G26


Input only items in blue

1.2438

Don't enter this! It is calculated from Wo, We, and other Useful Load Group items

Calculated Empty Weight constant "a". Go to Initial Sizing Inputs sheet and revise value in purple box:

ASPECT RATIO OPTIMIZATION: DR-4

A-baseline 6.3Wo 0.2Wwing-base 276We-base 1255.1 Read performance results and enter here

A A/Abase Delta We We-new Range ROC6 0.95 0.97 -8 1247 1165 212 175 2200

6.3 1.00 1.00 0 1255 964 220 180 240014 2.22 1.61 170 1425 760 221 181 2500

Wwing/ Ww-base

Max Speed

Cruise Speed

Enter delta on Weight sheet (I stuck it in the unused Anti-Ice entry), and change aspect ratio and empty weight "a" factor on Initial Sizing Sheet

6 8 10 12 140

500

1000

1500

2000

2500Aspect Ratio Trade Study

RangeMax Speed *10Cruise Speed *10Rate of Climb

Aspect Ratio

nmi,

kts,

or f

pm

max*10 cruise*102120 17502200 18002210 1810

6 8 10 12 140

500

1000

1500

2000

2500Aspect Ratio Trade Study

RangeMax Speed *10Cruise Speed *10Rate of Climb

Aspect Ratio

nmi,

kts,

or f

pm

copy of raymer simplified aircraft design spreadsheet (sam)

Documents

simplified aircraft design

empty weight constant

performance calculations

power loading

stall speed

volume coeff

sq ft

qc d0