8.3 - Engineet’s Computation Pad N0 5505 £3111...

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C .9 ‘6 ‘5 a E o 0 U) \— m m .E c» C Lu .[ow,/¢ >45} fig wry/w 97‘ wgra.7"1(z/£ (444;); jlWJ’w Z '0 5’24-JZ l3!»n/.// (—4 win, 54.; I #747! In city’r‘rjAmé’a/ M 22 a- 6x By an au azu u—+v-= v—5 6x By a) 9L 0y where v is the kinematic viscosity, defined as v52 p/ p. AM // Engineers Computation Pad No. 5505 @ Zflh- 41°44’7<"¢/ ji/ex’p" 75", zp‘n/A/y /4'/</ : Val/f In/y 74v 4 ‘75/(7/ ,a/(y, 9.4/7 lamb“, ’57A1/7/J by,” Z‘b/J/7l7q/1/ 4 44A, 5.1. 4/”; «xx/J (fi/ (An/Vt (SJe./m- :>/:£VHJ7L<PJ7L {/fita7t74/vJ5-z/o) : (Iniflq f => “Va - Mk Vt'r.‘1J 7- («’7‘ fih/ J'Jn. 24/, fl’quJ‘p/V )/-/-vn7‘ In an ~ ML, (VJ/.94. ( A2, 3 77¢ y- (pp/r63».( 7: 'fl/Urw U (' Jrh/é flflf Ann/1%”; ~ (“fl/bx 547‘ 9% P05 3, 5,4; flahM>./4, .O gr.///(0(L y‘F 5/‘K./rr’ Jy/67()h xi“ .5 fl , g jy/yL ‘/Z 154’: Vivtt "w {5‘ 8 hp‘fi'IKAQO-DJtv—‘t/ ‘C 7 we ,, V (’Ir/vhi ‘4 d’ Vii» 47V; 33’ king/7f; 7Q, 4// firjfiéé {o/ /@ 6’A ééhyf’”J. will} Lil‘/ :K’m 70.27% Infvéanafi' 7; I, 04X) 2 L W1!" 547“ 3% “I E 7:“ 7%)“? (j) glpts/ jfi‘w'7<)< 7!: {5-0674anJ 52% X‘ v(x10’) 'AUI‘OJOM ‘ | Alt-0.10m + 2'0 2,.Ili0505/s‘0 m 6-0.5x13‘m + I Ant-0.05m 0,-40m/I I A! 1:0 5'5-7“°"m + u,-40m/s U.-40m/s + Lo .4. --—-’ + ——D ~ + . "Q summon“ 5"3.3x10“m + 6 '45le m —-——’ Figure 4.6 Velocity profile for the flat-plate laminar boundary layer Rer = 5.477 x 10’. 6 5 >"I 3‘ 4 3‘ n 3 p 2 1 FIGURE 17.8 0 0‘2 0-4 0-6 0-3 1-0 Incomprcssible velocity profile for a flat plate; solution of f'(n) = 11/ V... the Blasius equation. U TABLE 4.3 SOLUTION FOR THE LAMINAR BOUNDARY LAYER ON A FLAT PLATE 11 f f f" 0.0 0.0000 0.0000 0.4696 0.1 0.0023 0.0470 0.4696 0.2 0.0094 0.0939 0.4693 0.3 0.0211 0.1408 0.4686 0.4 0.0375 0.1876 0.4673 0.5 0.0586 0.2342 0.4650 0.6 0.0844 0.2806 0.4617 0.7 0.1147 0.3265 0.4572 0.8 0.1497 0.3720 0.4512 0.9 0.1891 0.4167 0.4436 1.0 0.2330 0.4606 0.4344 1.2 0.3336 0.5452 0.4106 1.4 0.4507 0.6244 0.3797 1.6 0.5829 0.6967 0.3425 1.8 0.7288 0.7610 0.3005 2.0 0.8868 0.8167 0.2557 2.2 1.0549 0.8633 0.2106 2.4 1.2315 0.9010 0.1676 2.6 1.4148 0.9306 0.1286 2.8 1.6032 0.9529 0.0951 3.0 1.7955 0.9691 0.0677 3.2 1.9905 0.9804 0.0464 3.4 2.1874 0.9880 0.0305 3.5 2.2863 0.9907 0.0244 4.0 2.7838 0.9978 0.(X)69 4.5 3.2832 0.9994 0.0015 Drag coefficient 10- 31.4 Drag coefficient versus Reynolds number for NACA 64A004 LAMINAR FLOW \\ Pr(///,'¢7‘//r-IJSI5‘ \\* 7:17/4’64/ ’7.r“""/I// \ Corrected Blasnus \ lat plate result) Blasius flat plate ale XFOIL data points 106 Reynolds number LE ...
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This note was uploaded on 04/07/2008 for the course AE 2020 taught by Professor Ruffin during the Summer '07 term at Georgia Tech.

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8.3 - Engineet’s Computation Pad N0 5505 £3111...

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