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    Experimental Studies of Radiative Base Heating of a Jovian Entry Model (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: To verify the validity of the theoretical predictions of Park on radiative base heating rates, two types of models are tested in the absence of ablation in shock tube flows which simulate the Jovian entry environments. The radiative fluxes are measured by pyroelectric radiometers imbedded in the models in a stream consisting of 10% hydrogen in a bath of either neon or argon. In addition, time-resolved photographs are taken to obtain information on the structure of base flows needed in Park's theory. The experimental data show that the radiative base heat fluxes are significant fractions of the radiative fluxes at the front stagnation point, the ratio being dependent upon Mach number and the configuration of the models. When the effects of the model geometry and Mach number are accounted for, the present experimental results agree with the theoretical predictions of Park.
    Keywords: Lunar and Planetary Exploration
    Type: AIAA Paper 79-0038 , Aerospace Sciences; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA; United States|Entry Heating and Thermal Protection: Progress in Astronautics and Aeronautics; 69; 148-171
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Modeling of Radiative Heating in Base Region of Jovian Entry Probe (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A theoretical model is derived to determine the average thermodynamic properties in the expanding region, recirculating region, recompression region, and neck region through application of one-dimensional conservation equations. Radiative transfer is calculated using spectrally detailed computer codes accounting for nonequilibrium. The results show that the most severe heating occurs immediately behind the frustum, and that the recompression and neck regions are the major sources of radiation that heats the base stagnation point, The radiation flux to the base point is slightly stronger with ablation than without. Its value is 0.11(43 P(sub b)/P(sub s))(sup 2) times that to the front stagnation point where the base pressure P(sub b) is defined as the average pressure in the recirculating region and P(sub s) is the front stagnation-point pressure. The time-integrated heat load to the base point is 18(43 P(sub b)/P(sub s))(sup 2) kJ/sq cm.
    Keywords: Lunar and Planetary Exploration
    Type: NASA/TM-1979-207857 , NAS 1.15:207857 , AIAA Paper 79-0039 , Aerospace Sciences; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA; United States|Entry Heating and Thermal Protection; 69; 124-147
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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