By Michal Lunc, P. Contensou, G. N. Duboshin
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An Estimate Chemical Space Heat Rates in GasPhase Combustion with Applications to Rocket Propellants, Paper No. 824-59, American Rocket Society (1959) 7 TORDA, T. E. (1959) * TORDA, T. , Combustion Instability of Liquid Propellant Rocket Engines—Notes on the State of the Art and Proposed Areas of Investigations presented to the AFAOR, Jan. 1962, Armour Research Foundation TM D-29 5 58 T. P. TORD A and R. L. MATLOSZ 9 COMBS, L. , Calculated Propellänt Droplet Heating Under F-l Combustion Chamber Conditions, Rocketdyne RR 64-25 10 WIEBER, P.
Example for unfavorable coil arrangement 0 0,5 1 1,5 ^ Fig. 8. Penetration of the field as a function of dß. d—coil diameter, λ—wavelength 38 W. PESCHKA and R. 1 m we get for different wave lengths A the radial field distribution shown in Fig. 8. e. if λ <^ 2nr, we have an essentially higher field intensity near the coils than along the axis. In Eq. (4) 70 is the modified zero order Bessel function. The problem of penetration into a plasma can be dealt in approximation by the aid of the classical skin depth7 if the free path of the particles especially that of the electrons is short compared to the dimensions of the discharge vessel which is normally the case if we have pressures higher than 10" 2 Torr.
The results of the energy balance analysis indicated that the energy contributions from radiation and from the heat conduction through the thermocouple are small (approximately 2 to 3%) compared to the energy requirements for vaporization and superheat. Two main conclusions were drawn from the analysis: (1) the analytical model (quasi-steady) is not valid for droplet vaporization at high temperatures and high pressures, and (2) a nonsteady analysis using the energy, momentum, species, and global continuity equations is required to solve this complex problem.
Propulsion Re-Entry Physics. Proceedings by Michal Lunc, P. Contensou, G. N. Duboshin