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Plane-flame simulation of the wake behind an internally propelled vehicle Part 2, simulation of a supersonic vehicle by a heat…

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5 2. EQUATIONS OF MOTION The characteristic equations for one-dimensional nonsteady flow including friction and convective…
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and Jh~ is the film coefficient of conductive heat transfer; ~ 1.. =- K c..~ \? c.,. \ LJ.... ~ - LA.. \ 2-. 6 (5) (6 )…
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3. RESULTS Equations (7), (8) and (9) have been integrated numerically using a finite difference technique on the IBM Systems…
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8 flow that never returns to ambient conditions. On the other hand, when friction and heat transfer are accounted for, this…
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9 convective heat transfer rate is always higher close to the heat source than further downstream. Therefore at any instant…
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10 this region of the flow is steady in a frame of reference fixed to the detonation front. The subsonic heat source, on the…
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11 It can be seen that as time progresses these two families of curves are slowly approaching each other. When the flow…
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12 4. CONCLUSIONS The flow field induced in an infinite tube by a subsonic internally propelled vehicle is qualitatively…
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13 5, APPENDICES APPENDIX I Solution for Inviscid and Adiabatic Flow The steady flow equations for a one dimensional heat…
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14 the following iteration procedure is used. A first approximation to the Mach number of shock 1 is guessed at. Then using…
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15 APPENDIX 2 Construction of the Characteristic Grid A sketch of the characteristic grid for when friction and heat…
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16 APPENDIX 3 Solution When Characteristics Cross the Heat Source (Figure 10) Points 1 and 2 are two points in the time…
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17 Subscript 1,4 means that the flow parameters are averaged between points 1 and 4. Equations (A-7), (A-8) and (A-g) are…
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6. REFERENCES 1. Skinner, J.H., "Plane Flame Simulation of the Wake Behind an Internally Propelled Vehicle -- Part I -…
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19 TABLE I Results for Inviscid Adiabatic Flow U~ ~ o. S- T -::. \ 7... 0 \..j ~ -.:. ~·\9 Location U A pipo S Slope…
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INERT GAS REARWARD SHOCK (2) ~ FIGURE 1. INTERFACE I I I I I COMBUSTIBLE MIXTURE Gases at rest before ignition…
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50 ~ ~ ~ ~ ~ , INVISCID ADIABATIC - - - WITH FRICTION AND HEAT TRANSFER , 40 30 20 '" , " 10 o…
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1.0 0.6 -- - - - - - - - -.----- r=80 , 40 35 30 25 20 15 ------~~--~------~----~~----~----~~----~,Q5 o 10 5…
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4.0 T=/ T=5 3.0 T=IO T=20 2.0 T=40 T =80 - - - - - - - --------------------- L--_--L-----'---------L----....l…
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I t ~ Ik ~ """" T=80 """" I- f I 35 30 - - - - - I I I r r=20 r=40…
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T/To V/Vf I> "-"- "- _ T=IO I / / / / , / / / , / / / - / / _ _ T-20…
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1.4 1.3 1.2 1.1 1.0 0.9 0.8 0.7 0.6 0.5 0.4 0-3 0 5 10 15 T/ To 20 25 FIGURE 8. Pressure, temperature and…
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T c: FIGIJRE 9. Construction of characteristic grid
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T 2/ ____ _ I / \ / \ . 4 m... 1\ / \ / \ / \ / \ I - I \ 5 --- ------ 1. _ _ _ 13----6 -- b I U I t :…

Plane-flame simulation of the wake behind an internally propelled vehicle Part 3, experimental simulation of a supersonic…

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J. H. SKINNER VEHICLE WAKE SIMULATION PART 3
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