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Appl Aircraft Aero

by: Heloise Bernhard DVM

Appl Aircraft Aero EAE 127

Heloise Bernhard DVM
GPA 3.83


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Class Notes
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This 4 page Class Notes was uploaded by Heloise Bernhard DVM on Tuesday September 8, 2015. The Class Notes belongs to EAE 127 at University of California - Davis taught by Staff in Fall. Since its upload, it has received 55 views. For similar materials see /class/191754/eae-127-university-of-california-davis in Engineering Aerospace Sci at University of California - Davis.

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Date Created: 09/08/15
EAE 127 MIDTERM 11082005 Open notes open book 1 Inviscid Incompressible Flow past 3 Thin Airfoil 15 points l x x x The camber lme ofan a1rf0111s glven as dx gAail ij3 4i andA gt 0 c c c 11 Sketch the camber line in the Xz plane 12 Find the coef cients 140141142 from the in nite series solution A0 2Aquot cosnt d39 xt 06 n1 Hint Expand dx determine d x perform the transformation using i 1l cost and cos2 I l1 cos2t c 2 2 Check your results carefully as several results depend on them 13 Find the angle of adaptation 06mm and sketch the ow eld for 06 lt 06mm a 05mm and a gt 05mm 14 Find the aerodynamic coef cients 0 Cd and Cmyg x 15 Find the aerodynamic center x 5 and the center of pressure 5 p c x5 1 16 F1nd the angle of attack 06 for whlch p 7 c EAE 127 MIDTERM 11082005 SOLUTION Open notes open book 1 Inviscid Incompressible Flow past 3 Thin Airfoil 15 points 11 Sketch the camber line in the xz p1ane 12 Expanding dx yields 2 and d39xlA3 14112x 2i 3 K c c 2 3 dxlAc33 7x 24x 3i 3 K c c c Using the transformation 2 1 cost and the identity cos2 t 1 cos2t c A A A a x t cost cos 2t 6 3 2 Thus A0 2A cosnt d39xt 05 g 05 geosa geoth and the n1 A A coeffICIents An are found to be 06 g A1 3 7 A2 13 At the angle of adaptation madam A0 O 05 madam gt madam g 14 The aerodynamic coefficients are c1 271140 gt c1 27m cm0 A0A1j gt xcp x05 are and the center of pressure 0 x 1 for all th1n a1rf011s c xcip CLO gt x5 F A 0 cl 0 15 The aerodynamic center x 16 The angle of attack 06 for which 5 p l c l xi 10 A12 gt a 2 c 4 06 12 2 Linearized Supersonic Flow past a Thin Airfoil 15 points f39x fquotx7i 21Atot0 2 2 cx 7f x7ogi Ackeret I 3 02ltx7f 0071 22Atot A 0 f xia i 0 ckeret 020 f xiaii i


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