AE 3003 Final - Spring 1996 - Yeung

# AE 3003 Final - Spring 1996 - Yeung -...

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Unformatted text preview: -'-I':r*“'“"‘-“""3‘ “EEK s -. ia'v'i-iul n: g! 11E 311113 Spring 1996 Jill- Final Exam, Part I Closed Book and notes Answer each question concisely {in the space provided, if possible]. Make graphical sketches where they seem useful to illustrate your point. He clear and unambiguous. Except 1where noted otherwise, each question is worth 1 point in the ﬁnal grade. Turn in this part in approximately an hour, after which you can begin to work on Part II. 1. What does the quantity If pl? -ﬁ' do represent physically, and why does the dot product appear it'tsicle'iII cs Mrs-55 Haul Fol? J. '4'? [S ‘2. 'What is the difference between absolute pressure and gage pressure? 3. Explain the principles involved in the determination of drag ofa two-dimensional hody from measurements of the velocity proﬁles in front and behind {in the wake 0f} the body. "J— (a ll 55’ r' Lo?" up} if} i: ﬂit-Hm!“ t' WA 4. Suppose in a two‘dimensionnl ﬂow the velocity components u and s- are given. How would you use this information to obtain the equations representing stream- lines in the coordinate plane? Cl)“ is J. _.--" W M 5. 1|What is an irrotational vortex? What is special about the ﬂow at its core? (Sniff; 54'1““in "4 _-":ft-rf_ ._., _-|l"'l.r .2 (on: refra't . i -.4 5W”? “iii-1“? " WW” * + w n ' I.. "—" I/Wltﬂr I f r“ ti. State at! the necessary conditions for Bernoulli equation to to apply hoth along and across streamlines nooﬂW5ﬂ:k \$3717 at? {4/ I 1 if. can 5% 5 “5-3W%} {ﬁts-EEC? Errote‘ffﬂ’l" If! it'ﬁfcrdy “£27155, 1" . ﬁts discussed in class, in two—dimensional potential ﬂow both the stream function and the velocity potential satisfy Laplseeequation1 which is linear. What is the importance of this fact? [What has it allowed us to do?) ﬁﬁj sﬁuﬂe ﬂeas _. f - 7?) a 94%” 3 idrw'i",w i ”mi/5 3. Hour do you deﬁne the strength of a source? Include information on its proper dimensions. L .1 whose 776““ :— in; \$31er W .‘ Zr- 7/ scat *1 9. As discussed in class.‘ the case of uniform ﬂow plus a source can represent ﬂow over a sloping hill. How would you adjust the uniform ﬂow andfor source parameters in order to represent a higher hill? .31; If} {jg—lass?!" giiirfﬂ It]. In potential ﬂour over a cylinder the theory predicts the same pressure distri- butions in front and ”behind the cylinder. In what sense does this result violate reality? fri‘f’i'iﬂh (WW-€5- fq “if": {JP-{'5 “7' Trait/f"? 2 (mush-i ( I'.IHr 4L ble-i of 1]. Explain brieﬂy why airplanEs can ﬂy. 12. If the vortex strength distribution along the chord line of an airfoil [from leading edge to trailing edge} is known, state two lreyr steps you would use to obtain the lift force per unit span. If {'1 _ f ._ . , Jﬂl *2;ka I} l ff/ a“: J r” L5 13. What is the center of pressure? Where is it located for a. symmetric airfoil? .-— Lvd'ﬂrf LEE-1+ Gr (+9. g 1.4 .r'lLU'" Rufﬂe-i "41/ or.— 14. Explain how a. trailing 1Hotter: forms for a wing of ﬁnite span. Fists» [frkfmj rem" ﬁ'uf‘d two/3% 15. Explain why there is a negative downwash tlrelnrusitfp+ between the root and tips all EI- ﬁnite win; lﬂ_67lLtCF0( Df/ﬂpgifr/dﬁ‘ﬁl it; If“! Olﬂi'ré'h-j Vgﬁf‘l'i‘MJ 15. For what type of wing are the angles n, or and aha all independent of spanwise locations across the wing? Lint 5N] 1?. (2- pts] Explain how induced drag-arises, anti state two ways to minimize it [far a given lift] in wing design. (Jim: 7%? Wﬁﬂﬂ MFIMrﬂH“ ﬂjng/J 13. [2 pta] Make a carequ sketch that compares the variation of lift weﬁicient versus geometric angle 91' attack for {i} a symmetric airfoil [ii] a camber-ed airfnii and [iii] an unturiste‘d elliptic wing. ...
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