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  • 1
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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
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  • 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
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  • 3
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    MHD Energy Bypass Scramjet Performance with Real Gas Effects (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The theoretical performance of a scramjet propulsion system incorporating an magneto-hydro-dynamic (MHD) energy bypass scheme is calculated. The one-dimensional analysis developed earlier, in which the theoretical performance is calculated neglecting skin friction and using a sudden-freezing approximation for the nozzle flow, is modified to incorporate the method of Van Driest for turbulent skin friction and a finite-rate chemistry calculation in the nozzle. Unlike in the earlier design, in which four ramp compressions occurred in the pitch plane, in the present design the first two ramp compressions occur in the pitch plane and the next two compressions occur in the yaw plane. The results for the simplified design of a spaceliner show that (1) the present design produces higher specific impulses than the earlier design, (2) skin friction substantially reduces thrust and specific impulse, and (3) the specific impulse of the MHD-bypass system is still better than the non-MHD system and typical rocket over a narrow region of flight speeds and design parameters. Results suggest that the energy management with MHD principles offers the possibility of improving the performance of the scramjet. The technical issues needing further studies are identified.
    Keywords: Plasma Physics
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  • 4
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    Improvement of Scramjet Performance-Experimental Demonstration of MHD Acceleration (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: One of the critical technologies of MHD (Magnetohydrodynamics) bypass scramjet propulsion for space launch and cruise vehicles is MHD acceleration. An experiment in a shock tunnel is described in which MHD acceleration is investigated experimentally. The objectives, the methods used and the preliminary results are described in this paper.
    Keywords: Plasma Physics
    Type: 15th International Symposium on Airbreathing Engines; Sep 02, 2001 - Sep 07, 2001; Bangalore; India
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