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2005C Test 2 Solutions

2005C Test 2 Solutions - um 191 Test FIJI 1005 Hum'51"...

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Unformatted text preview: um: 191 Test: FIJI 1005 Hum: '51:" Lia-H can. I. {I'M-H Consider a rectangular wing at (I: = 10“. Th: span is I“ II. Th: chard in! ft. Th1: Hui-mat {N} v and Axial ML} [mm are Hlﬂ lb and 5 ll'l " I 1perpmdlcu|ﬂl and parallcl to IE1: wing I:th respectively}. Dulminc th: Trﬁ. L. and drug D. Forces. I" H L: ﬂgagn- ﬁlial-I: Ian-«aunt: - S‘ﬁnih "D: Patina ‘I' It"whammy-c. walla- I'nn'm. '1 I’m-cu]. 1.1:: J. g 6%} ﬂit-m1 1h: praisult. Pm. nu 1h: wing as nﬂmwn. when: x is measured I'mm I11: 'Itadqng :dgc, c=chnrdlllﬂm sea level mndlﬂuns {nun-1 fur Interprelaﬁnn by simple absen'at'mm the dislrihuliun is a simple gﬁumﬂry and pmx-jdcs you an uncapmb]: .-' my graphical appruuch In 301%] HJ Find 11'“: :uel‘ﬁcmnts [TL and CHIC;- [a'hout mldthmd {x - till] I'm :11: wing ﬁlm: In Ih: prcmm. L Eu. -' l:- : _ggi “hm L 'I 1': ‘ Ibﬁbﬁ-{h-Hl‘ﬁ d: in: fit,— . v.5 1:.“ E I In 1: 113m Elﬁn-Wﬁlt : Eun‘m I-h = ll" -; Ml"- uhm Mﬁy‘h - (Elana-115*": #1: CH; 111. 1r. E? , _=_ ‘1- 1 Ink” -. ‘muuStﬁt'iil‘ﬁu-la“ ﬂ 1 w. : luau-u L‘A'lﬁg‘ﬁ an]! : lama-Elam... IB- H < H; nﬂ'h. H - all"; Firm-ah: Mﬂmluﬁ' III-n Hg...- mid Jam-d.) {1} Find the center or presume. mp. rclia'l'i‘rc m Ihc Juding :dgn: using :11: :mrﬂinatc mum as dﬂﬁnﬂ’i. - '1? =—w-=~- «um-n 3. {NW-i A Film tube is munled in the test section are high speed nut-smile wind lumei. The pressure and Immature ﬂf'li'ﬂ.‘ airﬂow are I aim and 2'91} K. respectively. {a} lfthe ﬁuw valueity is 250 rrL'rs. what is die pressure mmumﬂ by Ihe Film lube? Earner-Hi“: MEI-fin i-‘F'l'ﬁt': in Hull.- unit—m iii-ms ‘ﬁ- . 34w. 2.: {a ‘= rim-sun m...“ M..="7’fﬁ'c:. “R..=1..I~'rh~. T“ = ETD-“K 111i Whll is the stagnation temperature? 1% -_ 1 4 2E f“: Lahlf-l clef-laud» “hm 4. {15%} ﬁts designed. a precisely mounted Firm-static praise measures a pressure difference. 5F. for an Iimrﬂﬂ ﬂying at high Iuhaoniﬂ 5|!de {M - 03]. Strain pressure is provided [tr-m sit-other suuree. a] Using the imtmyie and energy aquarium develop the equaling: to determine the aircraft Mach. number ihinl. "Merit MHDTH}. .‘L 13;- = = = wean“ 1-1 L a: = KC‘EH T— Th1 hi Develop the equat'iun IrI determine the calibrated airspeed. Yrs-a. 1_ 1 .. 1. h? 1f \ Mt _ 3:; — 3:... ‘i m- t 1 HLm Cl...“ “3 D‘s : qua-r5 'P... :2 1?; "rink Ve- _‘ Vex: 5. {5 \$3} The dynamic pressure is deﬁned as q = Derive an equaliuu for q = q {p,M]. 1 1. 'F' '1. __ q tﬁﬁm=ﬁmsﬁi 1‘3- q‘ EL 1. " 1 1;“ E: HS‘PE} Fensider jeetttrelpie ﬂew threugh a supersonic nmeie. resenreir I ettit {ﬁlﬂﬂniiﬂn} _ I]: . 1': Ft!- I Tel tan :1] Where in preuute lite ntnttitnumihmm. er ett'tl'ﬂ bl 1|.i'It’I'ttere it! lempeﬁtttlre the tttexit'l‘ltlt‘tt'ihmttl. or exit}: :3 Git-en epeeiﬁe measurements el‘p and '1‘ at the reset-weir and mm, and given the mat. {Act ttt the exit, limithe [NIH-ﬂ ﬂaw [titII } till the exit. Ag: Evil-l \J; Rg‘eexm 1: D LP? Efﬁcigil. '1', {Etna} Can-thin: Bernoulli’s equation and the deﬁttjtien efﬂte pressure eeel‘ﬁeienL C1,. to l'tl'ttl the equetien I‘e-r CL. all 11 function eFt'eLeeitauniy. 1 '1 c'1‘“? Bi “PEEL: “Fug i: "P'P-F Elf-g! h I “I i- - "v' v .' . C? = L = {L ‘- it what I: the IE}. tn stemtiett entut'tl'turte '3 Ni: DJ CPI: i. 1-331 is lite E'P tit freestrenm eendt‘tlene '3 ‘5]:ka ('13: t E. {Hﬁi} Feminine: In mug in a law meted 1Wittti unmel. 'ﬂte Mitre-i! shape It! lJ'te HACA [Hill]? [refer In the ﬁgure: given Item the text}. The Remotes number ie ti 1: 10“. 1:. Given [IH erref‘ﬁe'tent = Min. ﬁnd the Ingie ul'etleek. Ihe the: emfﬁeient. and lite ﬁlament coefﬁcient let cell}. at e: 53:" Cd2.nnaﬁ. Cﬁv‘”: I: h. Estimate the maximum value of MD. {—1 IL. in“ ﬁr "limb-h‘ il- ' ‘ u- u- ‘hﬂﬁT—yh' ". ad huh“. I.' The Meet: number is Increased to I13. estimate the new vale fer the liﬁ eeeleiettt. L ‘- £31. In. J- etty—“ﬁt «art: Inn-fut 1;..- un-utt by“ ‘11 um} A wing in lasted at standard sea lm! candil'mns. 3 —~ 0 ﬁ'Eﬁh'cum "-11-" ll ‘r'_ =?EH£ELM_ =ﬂ.TD;‘ir'l = Efdilﬁliumln'mﬂwiJ -: LEI}. Find ﬁle pressun: cucﬁ‘miem {Chi atpuim ‘3‘. tﬁll- Emu-m1. - M '5‘- 1 1 L?n-' \$6; E :Q; 1' nah-n {PTg-l'ﬁn 1:ch_+\£. “a- ?- T— E h T .- Illh" = t :1“; a r?" = ﬁr: E qr; 3:: “- W- 3““ 11 I11 Th: air is ﬂawed to ‘i-L = 1:10;: ML E 111+] ﬁnd IJ'LE rm.- pi'ws'ure coefﬁcient {‘p. at 'a'. ““ if“ 7 = 05'9")”: (EPA = C9. ' \$1431" "ii—Mi a LIT tﬁ Hui-.1 {Eu-M- m": cm. II'J [lﬂanjExtra cmdit. Describe d!‘ Mumben's pmadax. +‘hlnu1 Trim-Jr: nu ﬁrm}. 1 “ENE-“Hi HIE-turd tie-n3 Fm wlm speciﬁc applicnlinn did Hami Firm develop d1: Fitnl tube? 5A..» ﬂlb'fﬁlll*i a"; rig: 1'5 What an: the tum major adverse cunmuerucns nf ﬂaw swarming over an airfoil? 34:15 a; I'IEPI' "I; inn-ea“ in ﬁlm-.5 How was (Land-Lard] Euler mnnmmd m {Daniel} Bemoqui'.’ {anusium ﬁicnds. nu knowlndgch f Edi” mas and.” a: mum: gain-Mr Iii what cnumnr {per John Aﬂdmn] was the incliiun ufrhe ﬁrst dniigmd and hail! wind tunnel? L vii-3h “A. ...
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