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lecture_11 - 16.512, Rocket Propulsion Prof. Manuel...

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16.512, Rocket Propulsion Prof. Manuel Martinez-Sanchez Lecture 11: Radiation Heat Transfer and Cooling Radiative Losses At throat of a RP1-LOX rocket, evaluate radiation heat flux c P7 0 a t m = c D0 . 2 1 m = c T 3500K = O/F 2.2 = γ =1.25 M=25 g/mol o c x0 . 3 ± 8 1 4 1 2 HO . 3 = 2 H . 1 ± 2 co . 1 ± γ γ− ⎛⎞ = ⎜⎟ γ+ ⎝⎠ 1 throat 2 P 1 c P 38.85atm = co P 14.8atm = 2 P1 2 . 0 a t = m m m 2 H P5 . 4 a t = 2 co P4 . 3 a t = === throat c 2 T T 3111K 5600R 1 Assume slab if thickness L=0.9 t D 0.191m 0.63ft = = () co PL 9.2ft atm = 2 PL 7.5ft atm = 2 H PL 3.4ft atm = 2 co PL 2.7ft atm = 16.512, Rocket Propulsion Lecture 11 Prof. Manuel Martinez-Sanchez Page 1 of 14
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CO Fig 4-22 for CO gas only to 2400 R 2 f t a tm So, extrapolated to 9.2 ft atm, ( ) 2400R 0.1 ε ± at 2400 R. But ε falls rapidly with T. If we conservatively extrapolate linearly in Log ε (T). co ε would appear to go to ~ 0.005 or so. Hence, even though the gas is CO-rich, radiation by CO is negligible . 2 HO At , PL , Fig 4.15 gives T P1 a t m = 7.5ft atm = ( ) 2 Ho 5000R 0.18 ε= , and extrapolating a bit to T=5600R, . 2 0.15 ε ± Fig 4.15 gives for o correct for finite and higher , use 4.16. Here, for , there is some significant effect of w ε wT P0 , a t →= . m T w P T P w PL 7 .5f ta = PP 2 + . We have 12 38.9 25.5atm 22 + + == way beyond the graph.
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lecture_11 - 16.512, Rocket Propulsion Prof. Manuel...

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