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Project tubeflight : phase 1, feasibility study : final report for the period Dec 10, 1965 - Sept 9, 1966 prepared for the…

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G. b. c. r.r= ~ 1,1 J I \ ,...... , ~ I , ... '- .... ~- / / / / / 7 7 7 7 7 / / --- ~ ~ "…
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IIIA-5 the interaction that the nonuniformity of distance to the tube wall will pro- duce between adjacent spanwise elements…
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IIIA-6 The ground line is simulated by using an image airfoil and image jet-flap. One could calculate the flow field about an…
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the jet momentum coefficient and the radius of curvature of the jet as 'to {X) = J Uc c· 2 R(~) .Q.£.. C· L{ ~ (,X…
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IIIA- 8 Z(~) curve in) plane on which the singularity distribution is located. ~, L = element of and total curve length,…
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IIIA-9 (6) Vq~ere Ym(x) is the mean line position of the airfoil and the jet flap and t (x) is the airfoil thickness…
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IIlA-ID Combining the above relations, it can be shown (Reference 2) that / .' (11) (12) for 0 < x ( c, and yj (…
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IIIA- ill it is possible to explicitly solve this system of equations for ~ (x) and ~ j(x) (References 5 and 6). However, as…
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IIIA-12 equation (14) can be found by an iterative procedure which is defined as a (x) C J \' .... +1 Jx o [x-i…
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~ 1.4 ~ II. Ii.: III o ~ 1.3 o a:: cs ~ ~ 1.2 :» o ~ IL :l ",1.1 I- u l&J IL tL. III o 1.0 Z…
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2.S 2.0 .... ·z loS 1&.1 - () - IL IL 1&.1 o () 1.0 O.S ",- --.... ~ ~ /- mA-14 +100 +10 0…
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obtain an appreciable lift augmentation this airfoil must operate at a moderately high angle of attack. lIIA-l~ Similar…
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IIIA-16 4' x 6' subsonic wind tunnel. The proper wall boundary condition is being simulated by replacing one wall…
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Some nominal dimensions of the moving ground plane are Width--------- 20 inches Length----~--- 50 inches Beltspeed----…
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-CI) '" % U ~ ~ - 3.0 TUNNEL AIR SPEED BELT SPEEDS 0 o fp. X 100 fp. Ii - 9S fp. 0> 100 fp. 1.0…
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IlIA-19 Aerodynamic Characteristics ofAxis~etrical Bodies of Revolution Traveling Within Tubes In a stability and control…
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- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - , IIIA- 20 '1 - L . I __ 1 - x -t u ____…
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IIIA- 21 are the cross flow contributions to the perturbation potential, ~ . The solution for the axial-flow perturbation…
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IIIA-22 where ~ , cL ,etc. are called the stability derivatives of the body. elf> d h These derivatives are (Reference…
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Displacement or heave (h) a(Yt) clh = = { 4.O< ~ } - [I - 0<]2 '8~CSE of 'BOllY Li s' 2 2. B…
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CJ = h.1. C, . ~L/u C~ - b 16 [ SII:j'.,j 0<." :{O<M ( J - oeM)' - IJ ~ [- 9 + f O(M 3 (.3 -2…
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\2 \0 8 iBM LBUA-lo 6 C Lli '\ ~tv1-L '0 .. 4 2 o .I ________…
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10 8 6 4 2L---=~--- eM a eM I a «,,-0 o~--__ ~--~~--~ __ --~----~----~----~----~----~----~ o 0.1 0.2 0.3 0.4 0.5…
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IIIA- 27 PRELIMINARY ANALYSIS OF VEHICLE INHERENT STABILITY The present state of the art, relative to the determination of…
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IIIA-28 where F')t / F" , F. = scalar components of force acting on vehicle U V J W = " " "…
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