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  • 1
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    Radiative Viscous Shock Layer Analysis of Fire, Apollo, and PAET Flight Data (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Equilibrium, radiating viscous shock layer solutions are obtained for a number of trajectory points of the Fire II, Apollo 4, and PAET experimental flight vehicles. Convective heating rates calculated by a benchmark code agree well with two engineering correlations, except at high altitudes corresponding to low densities. Calculated radiation intensities are compared with the flight radiometer data and with inviscid flow results. Differences as great as 70% are observed between measured data and the viscous calculations. Because of boundary-layer absorption, viscous effects reduce the intensity to the wall by as much as 30% compared with inviscid intensities. Preliminary chemical and thermal nonequilibrium flow calculations along a stagnation streamline for a PAET trajectory predict an enhancement to the radiation owing to the chemical relaxation. Stagnation point solutions are also presented for future aeroassisted orbital transfer vehicle geometries with nose radii of 0.3-15 m.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: AIAA Paper 85-1064 , Progress in Astronautics and Aeronautics: Thermophysical Aspects of Re-Entry Flows; 103; 514-540|Thermophysics; Jun 19, 1985 - Jun 21, 1985; Williamsburg, VA; United States
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  • 2
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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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  • 3
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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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  • 4
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    Validation of Multitemperature Nozzle Flow Code (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A computer code nozzle in n-temperatures (NOZNT), which calculates one-dimensional flows of partially dissociated and ionized air in an expanding nozzle, is tested against three existing sets of experimental data taken in arcjet wind tunnels. The code accounts for the differences among various temperatures, i.e., translational-rotational temperature, vibrational temperatures of individual molecular species, and electron-electronic temperature, and the effects of impurities. The experimental data considered are (1) the spectroscopic emission data; (2) electron beam data on vibrational temperature; and (3) mass-spectrometric species concentration data. It is shown that the impurities are inconsequential for the arcjet flows, and the NOZNT code is validated by numerically reproducing the experimental data.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-111818 , NAS 1.15:111818 , AIAA Paper 23-2862 , Journal of Thermophysics and Heat Transfer; 9; 1; 9-16|AIAA Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
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