The Possibility of Simulating in Wind Tunnels the Parameters of Hypersonic Flow and the Conditions in the Combustor of Hypersonic Scramjet Engine
Tóm tắt
The process of acceleration of air in a Faraday-type MHD channel is analyzed for a thermodynamically nonequilibrium model of gas seeded with an alkaline element such as potassium. It is demonstrated that the use of existing electric-arc gas heaters with P
0= 200 atm and T
0= 4700 K, in the presence of magnetic fields B= 12 T, makes possible an almost exact simulation of the gasdynamic parameters at the inlet to the combustor of a hypersonic scramjet engine (HSJE) in the range of values of the Mach number of the flight from 12 to 20 (direct connect mode). In so doing, the concentration of atomic oxygen O does not exceed 2%, and that of nitrogen monoxide NO, ∼5%. When the gas is expanded in the secondary nozzle to static temperature values corresponding to the conditions of free flight, an exact simulation of the latter is possible at an altitude H= 65 to 70 km (u= 7.5 km/s, M = 20 to 25).
Tài liệu tham khảo
Lineberry, J. and Chapman, J., MHD Acceleration for Hypersonic Applications, AIAA Paper, 1991, no. 0384.
Christiansen, M.J., Schmidt, R., and Chapman, J.N., Further Analysis of MHD-Acceleration for Hypersonic Wind Tunnel, Proc. 33rd Symp. on Engineering Aspects of Magnetohydrodynamics, Pittsburgh, 1995, vols. 5–1 and 5–8.
Miles, R., Brown, G., Lempert, W., et al., Radiative Driven Hypersonic Wind Tunnel, AIAA Paper, 1994, no. 2472.
Williams, G., Comas, G., Menrenven, C., et al., Energy Addition and Thermolization Issues in a Radiatively-Driven Hypersonic Wind Tunnel by Macheret, AIAA Paper, 1995, no. 2142.
Boudreau, A., Smith, V., and Daniel, D., Developmental Testing of Ramijet Scramjet Propulsion Systems, AIAA Scramjet Paper, 1993, no. 5121.
Alfyorov, V., On the Problem of Creating the Flow Conditions in Scramjet Combustion Chamber in Wind Tunnels, AIAA Paper, 1993, no. 1843.
Maus, J.R., Laster, M.L., and Hornung, H.G., The G-Range Impulse Facility a High-Performance Free-Piston Shock Tunnel, AIAA Paper, 1992, no. 3946.
Stalker, R.J., Recent Developmens with Free-Piston Drivers, Proc. 17th Int. Symp. on Shock Tubes, New York: AIP, 1990.
Eitelberg, G., Calibration of the HEG and Its Use for Verification of Real Gas Effects in High Entalpy Flows, AIAA Paper, 1993, no. 5170.
Anfimov, N.A., Kislykh, V.V., and Krapivnoy, K.V., Z. Flugwiss. Weltraumforsch., 1992, no. 16. p. 169.
Bakas, R.I., Tamango, I., Rizkalla, D., et al., Hypersonic Mixing and Combustion Studies in the GALS HYPULSE Facility, AIAA Paper, 1990, no. 2095.
Alfyorov, V., A Report on the Status of MHD-Hypersonic Ground Test Technology in Russia, AIAA Paper, 1993, no. 3193.
Tempelmeyer, K.E. and Rittenhouse, L.E., Status Report on the Design and Test Experience of Steady-Flow J × B Accelerator for Wind Tunnel, Proc. 5th Symp. on Engineering Aspects of Magnetohidrodynamics, 1967.
Alferov, V.I., Vitkovskaya, O.N., Rudakova, A.P., and Shcherbakov, G.I., Teplofiz. Vys. Temp., 1979, vol. 17,no. 1, p. 163.
Alfyorov, V.I., Dmitriev, L.M., and Egorov, B.V., Investigation of Physico-Chemical Processes in Hypervelocity MHD-Gas Acceleration Wind Tunnels, Proc. 33rd Symp. on Engineering Aspects of Magnetohydrodynamics, Pittsburgh, 1995.