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AE 2020 Test 2 - Fall 2000

# AE 2020 Test 2 - Fall 2000 - 36 Name MFLHAEI Ggrrjnu’ AE...

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Unformatted text preview: 36 Name: MFLHAEI Ggrrjnu’ AE EGZEI TeSt #2 i ll’ 131%) Part I ~ Closed Book . {5 pts ea) Deﬁne the following terms, explain any equations: [a a) Kutta condition ‘c— = Eli-FE.) o Hfﬂd'ﬂ-ﬂ +V‘LL 5.61-1qu“. :5“ Elug-h +h‘.¥ +1.1; Fiﬁ” it"s-NHL: J: git-ng‘n'b/ +rK‘I1liq5 tdﬂaﬁ. SI‘HBO‘JP'LLI"! LIL-ﬂ l 15 1:": *‘P‘e +Iu'il'rtj all?! («male t's. Lun'l-aﬁmﬁ +1.1 +r.~.."|.'n [El—£1?- ‘IE ‘5‘. J+D~jr~¢u+rﬁn FJT'. ‘3 ii} Helmholtz‘s vortex theorems I“: The unfit-ex 'F1-iﬁu-w_!n+ \$+£Cn5¥h .'-; rung+qn+ aid ﬂ.) A «anvil-t}: Fflawea-L (ammo-is ewei Do A "Fluid": ‘i-lvu houmﬂqn'cg or Perm a. Linn-q} [c.3441 ix! For naive-or D-_I.'r{—|;r|l1ﬁ'1lr e1 al‘vﬁﬂ car-talus; all: qJL-hhcckl The: W|U¢ o-F F‘l ~13 IH “Erna-Lin 'J" “”34 cal-”d 4.5 c] Aspect ratio _b_L i): EPEKJ'I ﬂ '3- 5 (5:: : “4“”3 Artie». d} Aerodynamic center Fri 1.} Humane-f 13w. AV! ﬂit-'thi Eu": RFUH¢+|IH~1 a; U... TH; 5,“: F4 when 3; .' . m (“eméﬂ-H 54“” +1“: P5P err. Inclthe‘ln-«l- o-F +L’u era F 54+th 1'5 TN cote rad" o ‘ ' ‘31 ﬂ 4:”, I?” "”1"“ (LT-1H1! - I'i" 11 [L-ln— r' bolt—h. SYW'ME L-rI'q mad (eat—n incited tux-LIT Forllﬁ 2. (it) prs) Deﬁne induced drag-What conﬁgurations that we have studied show a ﬁnite induced drag? TM \$9553 +lwglr LIS. ﬁgLIanﬁd'l'a-ﬁ OF +Lu|u Iliﬁlf'a‘ Grad i-ﬁduﬁfﬁl (lanai: FF Cf uteri-c r “Chord Jili+¢~th_ 1+:5 Pﬂrniiai 4-5 +'Lr'-t. {‘l’ﬁlﬁﬁrfcrhm ULIIeJ-LT, {ﬁnﬁi'aqm-h‘ss Milli-Lo F.‘m.Ii-c D4 :31": (9.59.5 :n Pr'angi‘i'ili it'll-Haj HM 'i'hu/‘I 1‘th tag Cii-‘pi‘llfni iii-If-A- d+'5rt-r.1buh'oﬁ. 3. [1D pts} Draw an airfoil diagram showing the ﬁ‘eestream 1velocity, demsh, geometric angle of attack, induced angle of attack, d component of induced drag forasection ufa ﬁnite wing. [3; l /{ '- et l. “thoL—os Name: ' in AB 252G Test #2 INSIDE} Fast 1] — Open Bank 1. {3i} p15) A thin airfoil has a camber line as shown below: an e—uJ L.1-'j.u\$l;‘l rrELFDlL'] in————e Find: a} Angle nfzete lift. in] Pitching moment coefficient at quarter chord. e} Aeredynatnie center. 5. tr "int-r" Name: ll’l Feb-tug Crusher 2. {3ft pta] a light plane is flying at an altitude where the density is. EDGE} alugafﬂ}. The wing has a Straight leading edge, a span nf25 feet, a rent chord length of 5.20 feet and a tip ehnrd length of 3. 15 feet. The-plane is in level ﬂight at 15G mph with the wing operating at :1 CL pf :15. Assume i5=t. a} What is the weight of the airplane? b) What is the induced drag on the airplane? e) If the airfoil aeetiene an the wing have a 243'! lift ennre alnpe ef utilﬁfdegree and a zero lift angle of attack ef~2 degrees, what is the gee-metric angle nf attack of the wing? . tee Mt attwt- tee _ G“) WEI’EK-lt-ELI‘F—‘l‘. (Eh—“,5 (T3ﬁ339a53 ”-2 Q-F‘tfs ‘e‘ ﬂg+ HAG ﬁiil-‘ég-lfﬁllit-l = H.151 H1 ﬁg) '- Vi.£'2.j){1.0253 = GENE-ea / E“- l‘terE t LtLt..¢1Il : lDLr.5-Hf L: -5(‘fL{-ne133 gieﬂrFt1)(12e-thshz){ 'Dl-f-S‘i-Ftt) L: welsh-P ’- 2‘1’4307 HQ. / 551‘ £25,459)?— Dt‘imnms = Ce; were Vein «42*- ? * Waite}: LB 1'— “a. LBJ CL 1.5. 1134,25! T‘tiaﬁra)" 'Dlz’zﬂ‘ ,/7/ t); = Leann; 3L‘/1Lne133.){ttDiet;)‘\[teu.zq) t, elf, teed ) adj: Qnt.l05 {3&3( ﬁr.) "— [3..-CJll'ﬂ {RC} (3.01%: tt-teoz’waa‘lﬂtﬁ‘t 1+ (iaﬂ'lar’n {ema‘h L i + .95) like — -————...— 1 LLSDl-lr‘rrecl fat": tit-drum Saladsi [3,“; @153] _1|IHITr.-)?- w; dug T—T- Eiiusern‘mea D f X: (c/ziﬁu-ccse¢‘i .36 -t‘) aﬁ: mﬁ Jain :.2,5 Elia-€31 z-m-isix-o‘i 5C”. ytﬂ‘h: arr—L 'i',=-'?—\$‘x a: , jg... -ED 11. -1 1333:, 1 --ﬁ: S ”rm-{case ‘lliﬁaﬁ O 3:. ___5 'ﬁ- —ﬁ'[5mQa-E}ﬂ 0 Gina: 3 b‘) C‘Vﬁwqtd—TVH(AI {5123/ A -. 1 W; _ {a . Tr- a F §f “:52an ?£‘fz)ih1niglﬂ ‘ O A?T-D C'MLFHZD ' :- GD [j Lam-i. Tilran; mEL'l-EDL‘Ima Ligama “l -D'J‘E‘ipl'cltj LL: Quﬁﬂ‘dwo\ ...
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AE 2020 Test 2 - Fall 2000 - 36 Name MFLHAEI Ggrrjnu’ AE...

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