windtunnellab assignment and laboratory 2012 13 new

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AEROSPACE PROPULSION & AERODYNAMICS - ASSIGNMENT 2

BSc Aerospace Technology & BSc Aeronautical Engineering

2012/2013 session MODULE I.D. : -!22

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PoC: MODULE LEADER: D(. 4inn Ci+ S,e$# 10+ 5.%is,.$%. Assignment 2: Wind Tunnel Testing Laboratory - Aerofoil odels

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This assignment contains 4 parts covering laboratory report structure, aerodynamic loadmeasurements, pressure measurements and an application question to take your wind tunneldata and use it to analyse a simple flight problem. Note that the lab report and the assignmentare integrated as one single report submission. The work conducted should be documentedas a formal report of no more than 3000 words.

REMEM'ER ",is is $n ee%"(oni% s=<ission ONLY. You may answer the analytical aspects with neat ,$n-(i""en%$%$"ions. However please answer the discussion sections with typed answers. S"$"e $n* (e#e(en%es in ",e "e5"

$n $ (e#e(en%e se%"ion (e<o9e "o ",e =$%. If you haven’t done so already, it would be worth learning how to use

the equation editor in Word to present your workings or calculations but hand written calcs scanned and inserted into the

tet is fine also. !se "I units throughout and where necessary estimate values from the literature citing the source. #

contents page must be included and pages numbered for ease of referencing where necessary.

N.'. A $ssi7n<en"s "o =e ,$ne in 9i$ ",e in $9$i$=e on '$%=o$(+ ",is is $n ee%"(oni% ONLYs=<ission+ ness #ie "oo $(7e in ,i%, %$se s=<i" $ CD o( $"e(n$"i9e isos$=e <ei$ 9i$ S,e$#(e%e"ion+ no"e ",$" ",is o%<en" is =o", ",e Assi7n<en" AND ",e $= ,$n o".

1 | a g e

!uthor" #r. $onny otts, %heaf &11'



Wind Tunnel Laboratory Objective

The objective of the present low speed wind tunnel laboratory is to reinforce

the principles presented in the aerodynamics part of the lecture notes and illustrate

the equations hold in the physical environment. The chosen set of wind tunnel

models are simple 2D aerofoils with symmetric profile. Studying these aerodynamic

bodies in the wind tunnel and collecting load and pressure data via the data

acquisition system will provide basic exposure to standard facilities and experimental

techniques used in aerospace engineering.

1. Lab Report Structure

The basic structure of a laboratory report should start with an introduction to set the

scene and provide background. ! section on e(perimental models, techniques,apparatus, methods such as )!*! aerofoils used, data collection techniques such

as pressures measured relative to a reference, pressure water manometer

apparatus, including the wind tunnel itself, methods used to vary measured aero

parameters etc. etc. resent tabulated form of data collected, which could be

removed to an appendi(. !ppropriate graphical representation of results in standard

industry formats, such as *+, *# plots. #iscussion of results moving beyond

description to add analysis and intuitive discussion on the meaning of the results with

regards to aircraft and flight. *onclusions should summarise the most important

points focussing on meaning of findings in brief rather than simply stating results

again.

20 <$(s

. Load !ata symmetrical "ir#oil

!!Note that the Spreadsheets you used to manipulate the data are required as part of your submission!!

Testingdegree increments)!*!001' symmetric aerofoil at '0m-s, !o! / to '0 changing angle by '-3

30m-s, !o! / to '0 degrees.

Plot Lift, Drag and PM curves against AoA for both speeds on three graphs

Plot L, D, M curves against AoA for both speeds on three graphs

*omment on what you notice about the graphs when you plot the coefficientscompared to the force graphs.

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=hat do you notice about the * curve between typical flight angles of attack, !o!

range / and 10 degrees. f the lift acts at the centre of pressure cp and generates

a moment about the cg, assuming the cg is directly at the strut chord position,

calculate where the cp 9centre of pressure: location is from the leading edge and

state it as a ratio to the aerofoil chord (-c, where ( is positive displacement from theleading edge.

10 <$(s

$. %ressure Tappings &odel

!!Note that the Spreadsheets you used to manipulate the data are required as part of your submission!!

Testing )!*!001' symmetric aerofoil at '0m-s, !o! 10, 0, 10, '0 degrees

30m-s, !o! 10 degrees.

Plot p data for $%m"s, AoA &'%, %, '%, $% degrees on separate graphs

Plot p data for $%m"s, AoA '% degrees from both mm( $) measurements and DAS

results on the same graph *DAS & data acquisition system+

Plot p data for $%, -%, AoA '% degrees on the same graph

Note that the p in this case is the pressure coefficient N). the centre of pressure cp

10 <$(s

*p 9pressure coeff: 5 9pmeasured pstatic: - pdynamic

pdynamic 5 0./ ( rho ( 67', rho 5 density of air msl 1.'3 kg-m73

Aou will be provided with a graph or an equation of ptotal and pstatic against velocityso you can work out the correct values to choose for static and dynamic pressure,

recall that,

ptotal 5 pstatic < pdynamic

8efer to the )!*!001' !erofoil with Tappings manual !B10' uploaded to

>lackboard, the ( position along the chord for each pressure tapping is listed in

tabulated form. !lso the TrapeCium 8ule is e(plained in a lot more detail in there too.

%o, calculate *+ using TrapeCium 8ule ntegration 9area between curves: for '0m-s !o! 10 degrees. 8emember your pressure 9normal: force is perpendicular to the

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chord so don2t forget to resolve your calculated value to the vertical to get your *+.

Then plot your *+ point from your pressure data for 10 degrees on the same graph

as the *+ curve from the load data. *ompare your *+ value to load data from the

other )!*!001' model tested, how does it compare, what are the differences and

whyD

)ote that the,

+ift - unit span 5 !rea between upper and lower surface pressure curves

i.e. *+ - b 5 sum of cp areas along the chord c

where b is the span of a wing.

10 <$(s

4. "pplication 'uestion

f the '# aerofoil section tested was selected as a possible profile for a wing section

that could be strapped to your shoulders to enable you to become a human

aeroplane, assume you would be wearing roller blades as a simple means of having

an undercarriage. !ssuming your weight was E/kg and the weight of the wing was

'/kg and assuming you have unlimited thrust, using the data you have collected

from the wind tunnel present the information necessary including calculations,

workings etc. to show what the design parameters 9chord, span: of your wing needto be for takeoff, cruise and landing. #iscuss a number of different wing

configurations including high and low aspect ratio alternatives. #on2t spend too

much attention to the induced drag that you would e(pect on a finite span wing,

assume the lift per unit span is the same along the entire span.

erhaps a good starting point would be to look at what the span would need to beto lift you off the ground at a small angle of attack.

Fve deliberately left this Guestion open ended so you have the liberty to investigate

various possibilities yourself, there is no single right answer, you should be looking tooutline your discussion with simple calculations and inputs from your *+, *# graphs

to back up your arguments. have given it a weighting of '/H of the overall

assignment so please provide a fairly comprehensive and detailed answer worthy of

a quarter of the marks.

2 <$(s

N.'. A $ssi7n<en"s "o =e ,$ne in 9i$ ",e in $9$i$=e on '$%=o$(+ ",is is $n ee%"(oni% ONLYs=<ission+ ness #ie "oo $(7e in ,i%, %$se s=<i" $ CD o( $"e(n$"i9e isos$=e <ei$ 9i$ S,e$#(e%e"ion+ no"e ",$" ",is o%<en" is =o", ",e Assi7n<en" AND ",e $= ,$n o".

/ | a g e !uthor" #r. $onny otts, %heaf &11'



Assignment Submission

ELECTRONIC SUBMMISSION ONLY

Preferably submit your work in te form of an ele!troni! re"ort #in eiter $%o!&' $"%f format(

)ia te Bla!kboar% link$ If te file is too lar*e' an% ONLY if te file is too lar*e' alternati)elyyou !oul% submit on eiter a C+,+-+ )ia te Seaf re!e"tion alon* wit a !om"lete%

assi*nment !o)er seet$ If you submit usin* Seaf re!e"tion' "lease ensure you submit your

work on or before ."m /ri%ay "rior to or on te an%0in %ate s"e!ifie% in te assi*nment brief$

/inally' make sure all your %rawin*s,ima*es,"lots are !lear' rea%able an% are a!!om"anie% by

a written e&"lanation$ Submissions may well be multi"le file #most likely $&ls( wit su""ortin*

s"rea%seets to outline any !al!ulations' !larity of "resentation is essential to enable assessor

to follow a lo*i!al route trou* ea! seet$

Note failure to submit your assi*nment by te an%0in %ate will result in a non0submission

an% a mark of 1ero will be re!or%e%$ E&tensions to te assi*nment an%0in %ate !an only be*rante% by your Stu%ent Su""ort Mana*er$

If you %o not make a 2)ali% attem"t3 in any of te assessment tasks in te mo%ule you will

fail te mo%ule$ 4 )ali% attem"t must %emonstrate en*a*ement wit te sub5e!t matter of

te assessment set6 for e&am"le' tat some or all of te assessment !riteria an% learnin*

out!omes are "artially or fully met6 an% it must be !a"able of !arryin* a mark$

Minimum Pass CriteriaTe minimum "ass !riteria for tis assi*nment is .78' tis may be a!ie)e% by !om"letin*all or some of te assessment tasks "re)iously %es!ribe%$

IMPORTANT: Normal University regulations regarding cheating !lagiarism and

collusion a!!ly any student"s# deemed to be in breach o$ these regulations %ill be

re&uired to attend an Academic Conduct Panel and this may result in a $ailure o$ the

module'

Please refer to tt"s9,,stu%ents$su$a!$uk,re*ulations,mis!on%u!t,Ceatin*

8:7Re*ulations8:7:7;;;:$"%f for %etails on te Uni)ersity re*ulations re*ar%in*

!eatin*' "la*iarism an% !ollusion$

I | a g e !uthor" #r. $onny otts, %heaf &11'

https://students.shu.ac.uk/regulations/misconduct/Cheating%20Regulations%20201112.pdf







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windtunnellab assignment and laboratory 2012 13 new

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