2005C Test 3 Solutions

2005C Test 3 Solutions - AERO 20] Test 3 Fall 2005 Name...

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Unformatted text preview: AERO 20] Test 3 Fall 2005 Name 59‘ «A or} 1. 5% Sketch drag coefficient vs Mac for an airfoil, showing subsonic, transonic and supersonic trends. Show Mcr and Mad. Also, indicate the profile and wave drag components. 2. 10% A sonic boom is heard due to the oblique shock wave of the shuttle. At that instant, the actual Mach number and line-of-sight distance are measured. Estimate the altitude. .J ~e7’lA~-— 5"“ \n L _ r \lb fist/‘17“: Mm "Us, Since the shuttle has a blunt nose and a thick wing which affects the Mach wave, how will your altitude estimate will be affected? Elan-\— nose \mcreaS¢S Qwslfl i E> . Ember angle ‘3 relalca 'l'o lawn" Maw cocr Moo 94536545 \A'\K‘:‘)\A€r oA’riluda. 3. 10% Assame the wing on a supersonic aircraft can be represented as a rectangular flat plate and wing tip effects are negligible. The aircraft is flying “straight and level” at Mach 2 at sea level. The wing area, S, and weight, W, are known. Calculate the lift, angle of attack and the wave drag of the wing. Wv> CZW L", Lwig gang: cu- F.” : w :> was 4 Explain. If the drag coefficient decreases with Mach number for supersonic flight, then how can the drag increase? ' S 3 (SW?— / C‘\'\'\r\up\.¢3‘_\ COLA) éticre::1\ but“. Mao J i‘\V\CV-€QWS H, 4. 10% State the equation and sketch a drag polar (CL vs CD) for an airplane. C1 '2 D °° «6A1 CD. ' n_e*AE On the plot, show the contribution of induced drag to the total drag. Describe how one can find the Oswald efficiency factor from the curve ifiha wing geometry is known. C 3 e * ' CL ‘1'. C + .....__._ " Co 9° we“ A2 Co 'Cocbfi’hfi a (Pdmi' gives CLQ CD; Clob KKMKQ CL— " 0 Describe parasite drag, CDe , and its relationship to CD0 and CD]- for an entire airplane. C-De 7‘ CDQ'F Y‘CLZ rm ea An C MBA mum (33w an \ ZOOM. :véevjls MGM-r9) -Cuse\o,a£)ek\ S. 15% Consider aircraft flight along a straight and level (horizontal) flight path. Assume Vm is NOT constant (horizontal acceleration at 0), thrust is not aligned with the flight path (orT is NOT zero), and the wing angle of attack, is greater than zero (or > 0)‘ Draw a free body diagram of the airplane, properly showing the four principle forces, and from F = ma, derive the two equations of aircraft motion using a coordinate system that is parallel and perpendicular to the flight path. L. T $T2M§HI - 'D «EH-“3% "‘ LEVEL 1&an w _ Om¢© 6. 10% An airplane is flying straight and level, sea level conditions at constant velocity, Vm, and at (L/D)max. The total lifi, total drag, wing area, and aspect ratio are also known. Find the Oswald efficiency factor. Q4» b.\ (or Bl\> CD ‘2: CD: 4" CD: ==7 Cg '= ZCDD‘: 1C6: = 2' T—FéAfi a: 7. 15% Given: atypical PR curve of a jet powered airplane, and given W, S, CDC, AR, and 6*. List the steps (with equations) required to find points along the curve. GSSU ML co Assume a jet engine with thrust, TA, is provided. Show PA on the figure and show Vmax and Vmin. And, on the curve, show where CL, induced drag, and parasite drag are the maximum. 8. 5% On the given set of axis, sketch the lift vs at curves for both an airfoil and wing (made of the same airfoil profile). Indicate the on for zero lift, stall, and lift curve slopes (a, a0). GMFe" \ Lei war 9. 15% A wing is tested at V,o at standard sea level conditions. a wing: rectangular planform, S = 2.0 fiz and AR = 5 m- » m Test measurements are given in the table: Assume the tunnel width greatly exceeds the wingspan. Find the profile drag, span efficiency factor and the lift curve slope for the alrf011 section used in the Wing. g) D 4. Cd Ligand afl' 1:010 “9* CD: Cé a), w; 3 L51? ’D=.ZQ (d: nus/90$ Q. Lauua‘ firm Cd'k «Av M=b° LT-ls ’Dsfg ii: viii-"e— S) a S°\u< cur a AC» L‘s/37$ ’ 0) c>..= cit-em 3 we Cw a» mm a ’ a"; ' m3 Assume the tum are moved inward so that all wing tip effects are eliminated. What is the lifi at on = 6° if all other test conditions are maintained? mono \¢>o\(&” “Kt AK Q‘W‘éc’“ 0 ow: “~55 :7 ACfiactw—e WW; 9&3 Lot #3 1 ‘ Or a K new I A-ba-K 10. 5% Given the W, S, and CL, MAX of an airplane, calculate the stalllng speed at sea level. , uw-aoscm it»ch L yifm \ijL C‘- M W ...
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This homework help was uploaded on 03/25/2008 for the course AERO 201 taught by Professor Strganac during the Spring '05 term at Texas A&M.

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2005C Test 3 Solutions - AERO 20] Test 3 Fall 2005 Name...

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