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Tubeflight power-demand tests and initial validation of theory

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INTRODUCTION An analysis of the expected performance of full scale Tubef1ight vehicles is developed in Ref. 1 for the…
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2 NOMENCLATURE, ASSUMPTIONS, AND APPROXIMATIONS SYMBOLS A d h L v p P Re S t .J. t" u w f o f r cross-…
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3 Subscripts O,a,b,c,d,e See Fig. 1. i local stations along transfer passage (betw'~~n@a:hd®) t tube v vehicle…
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GENERAL PERFORMANCE EQUATIONS The required propeller thrust is (Pd - pc)At · In steady motion, Fv ( pd - fc.) At ::: = Ff -…
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5 The pressure drag Fp is not, in this case, a buoyancy drag. It is, however, still (6) This component of the drag, which…
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6 Finally, Fv (pd - pc)At AtA!Av {& Cf 7\"dv Lv t ( ~~ -1)Av + .o~tu: +.025 jJ 1 ~'~:I {guf ~: + ~: -1)Av…
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-m ....J .. > u.. .. (!) « B: 0 W ~ en « B: « Q.. ....J « ~ 0 ~ 60…
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,.. v 0 o· 10 9 8 7 0 6 5 4 0 0 0 0 - a laJ a: :) o laJ a: a: laJ :. o Q. 2 0 - 0 9 8 7 6 5 4…
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APPENDIX A BOUNDARY LAYER DISPLACEMENT THICKNESS GROWTH ON VEH~CLE AND TUBE WALL SURFACES A. Boundary Layer Flow of an…
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10 Therefore the velocity distribution has the truncated form ..L ~~J (1::r At Y 0, u Ut, so that I t~~1 ~t~af or a…
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The continuity equation which must be satisfied at all points in the flow is: aU ax + OV dtJ o 11 (3) The momentum…
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12 A control surface 1,2,3,4 is placed in a region of flow near the wall. The boundaries 1,2 and 3,4 lie parallel to the wall…
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13 friction equation can be written: (9) From Eqs. (8) and (9) one obtains ( ) _ j dFw 1'0 X - S dx (10) which is…
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14 . the local skin friction coefficient is a function of only the Reynolds number of the flow. As the 1/7th power law for…
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15 Integration of this differential equation from the initial value t* = 0 at x = 0 yields: t\x) = .232 ( ) 2 _I 7 71.1…
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16 Fig.A-~ compares the displacement thickness growth for u t = 0 and for u t 100 fps, where the undisturbed stream velocity…
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Assume u co = 225 ft/sec. The transition from laminar to turbulent boundary layer occurs at Re ·t crl Therefore, x . cr~t…
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18 obtained. From the previous analysis the following major results were obtained: 0.186 Xi ( )2 C~ 7 7 ( :£ ~J and 6X…
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19 1.2 , . . . . - - - - - - - - - - - - - - - - - - - - N I 0 )( 1.0 - -.. en en L&J Z .8 :lie:: 0 :::t:…
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DISPLACEMENT THICKNESS GROWTH ON TUBEFLIGHT VEHICLE AND WALL WRITE (3,85) 85 FORMAT (/1 6X, 'X', lOX, 'V…
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DISTANCE ALONG WALL, X tIft 2 4 6 8 Ly= 8 ft u.,FPS 0 225 N 2 • 0 150 ac 4 0 100 - - 6. 50 - UJ UJ 6…
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DISTANCE ALONG WALL, ft 2 4 6 Lv= 10 ft uoo,FPS 0 225 N 2 • 150 0 )( 4 - 0 100 - b. 50 en 6 en w Z…
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DISTANCE ALONG ,ft 2 4 12 14 L = 14 ft v uCD,FPS 2 0 225 C\I I 150 0 )( 4 0 100 - - l::. 50 U) 6 U)…
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-en 4. LL. - .. LIJ C) <t en en « 4. a: LIJ LL. en z C[ a: t- 4 AU 50 a 50 z La.. o 15 0 >-…
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APPENDIX B ESTIMATE OF VISCOUS FRICTION ON VEHICLE AND TUBE WALL SURFACES y I I X· I Fig. B-l. U· I --~>-~ X Let L…
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