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Unformatted text preview: Spring 2004 Uniﬁed Engineering
Fluids Problems F3–F4 F3+F4. A symmetric airfoil has a trailing edge ﬂap, with the hinge at xh /c = 0.75, with the ﬂap set at some small downward deﬂection angle ∂ . a) Deﬁne and sketch the camberline-slope dZ/dx, both versus x and versus α . b) Use Thin Airfoil Theory to determine the airfoil’s c� and cm,c/4 , as functions of � and ∂ . c) Important quantities for an airplane-control designer are the ﬂap control derivatives �c�
�∂ , � cm,c/4
�∂ Determine these for the present ﬂapped airfoil. Note: You may wish to check your results with Xfoil. The GDES menu allows you to set a ﬂap deﬂection. ...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05