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Aerodynamics: Aileron Reversal Analysis

1. The document provides information about a wing section in a wind tunnel experiment including span, chord length, static pressure, and air properties. It then gives equations relating lift coefficient to angle of attack and pitching moment coefficient to angle of attack. It asks to calculate the aileron reversal Mach number. 2. It instructs to create plots of aileron elastic efficiency versus normalized dynamic pressure for various values of another normalized parameter. It provides plotting guidelines and scale ranges. It then asks questions about features of the plots, including where reversal occurs and design implications.

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lamborghini1991
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273 views1 page

Aerodynamics: Aileron Reversal Analysis

1. The document provides information about a wing section in a wind tunnel experiment including span, chord length, static pressure, and air properties. It then gives equations relating lift coefficient to angle of attack and pitching moment coefficient to angle of attack. It asks to calculate the aileron reversal Mach number. 2. It instructs to create plots of aileron elastic efficiency versus normalized dynamic pressure for various values of another normalized parameter. It provides plotting guidelines and scale ranges. It then asks questions about features of the plots, including where reversal occurs and design implications.

Uploaded by

lamborghini1991
Copyright
© © All Rights Reserved
We take content rights seriously. If you suspect this is your content, claim it here.
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Download as PDF, TXT or read online on Scribd
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1. A uniform rigid wing section of span 1 m and chord 0.

2 m is suspended in a wind-tunnel as
shown below. For the wind tunnel, static pressure and air specific heat ratio is given as
p = 40 kN/m and = 1.4, respectively. For
2
1 5 . 5 M C
L

per radian, and



L M
C C 25 . 0 , calculate the aileron reversal Mach number.







2. UsingExcelorMATLAB,plotafamilyofcurvesthatdepictstherelationshipoftheaileronelastic
efficiency,E,versusnormalizeddynamicpressure
D
q q q , for various values of
D R
q q R
and 1 0 q . You should make two plots on the following scales to reduce confusion:
a) Plot 1 R using axes 3 3 E ,
b) Plot 1 R usingaxes 3 3 E .
Hint:Donotcomputevaluesforthecaseswhere 1 . 1 1 R ; Excel does not handle these well.
For some cases you may want to plot symbols only and nicely sketch the lines that form the
curves.
Answer the following questions: Where does aileron reversal occur? If you had to design a
wing what R would you try to approach and why? What happens when
D R
q q ? How does
the efficiency change as q approaches q
R
? Why do you think this happens? What other
pertinent features can you extract from these plots? Explain how you came to these
conclusions.

K
1
=5.6KN/m K
2
=4KN/m
x
2
=0.7c

U
x
1
=0.1c

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