Abstract
After an introduction into different types of high-enthalpy hypersonic ground test facilities the performance of the shock tunnel is described in detail with special consideration given to the Aachen tunnel. The basic shock tube performance is presented with numerical calculations using an equilibrium air model. The influence of boundary layer effects and van der Waals driver gas effects on the shock tube flow is included. Numerical calculations of equilibrium and frozen air flow in the nozzle are shown. The relaxation zone behind a bow shock is calculated using the air model together with 34 elementary reactions. The attainable simulation parameters are discussed. The experimental methods cover the measurements of pressures, forces and moments and heat flux; time resolved flow visualization is possible. The experimental results given include nozzle calibrations and a study of the nozzle starting process. A table is included giving properties behind incident and reflected shocks at initial pressures of 0.01, 0.1 and 1 bar for equilibrium air.
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References
Charwat, A.F.: A survey of hypersonic problems and the characteristics of shock-heated tunnels, ZfW, 8, 125– 134 (1960).
Wittliff, Ch.E.: Short duration facilities. Short Course in Hypersonics. State University of New York at Buffalo, Calspan-UB Research Center. August 1986.
Russo, A.L.; Hertzberg, A.: Modifications of the basic shock tube to improve its performance. Cornell Aeron. Lab., AD 162251 (1958).
Davies, L.: The interaction of the reflected shock with the boundary layer in a shock tube and its influence on the duration of hot flow in the reflected-shock tunnel. Part I. Aeron. Res. Council C.P. No. 880 (1967).
Grönig, H.; Schumacher, H.: Experimented Untersuchungen an Raum-flugkörpern im Hyperschallbereich. Teil II: Entwicklung und Aufbau eines Stoßwellenkanals mit erweitertem Leistungsbereich. Stoßwellenlabor, RWTH Aachen, BMFT-FB W 75–22 (1975).
Hertzberg, A.; Wittliff, Ch.E.; Hall, J.G.: Summary of shock tunnel development and application to hypersonic research. Cornell Aeron. Lab. Rep. No. AD-1052-A-12 (1961).
Dunn, M.G.: Experimental shock-tube investigation of conditions behind incident and reflected shocks in air for shock Mach numbers between between 8.5 and 16.5. Fifth Hypervelocity Techniques Symposium, March 1967, Denver, Colorado.
Wittliff, Ch.E.; Wilson, M.R.; Hertzberg, A.: The tailored-interface hypersonic shock tunnel. J. Aerospace Sci. 26, 219–228 (1959).
Warren, W.R.; Harris, C.J.: A critique of high performance shock tube driving techniques. In: I.I. Glass, Ed.: Shock Tubes. Proceedings of the Seventh International Shock Tube Symposium. University of Toronto Press, Toronto and Buffalo, 1970, pp. 143–176.
Glass, I.I. Ed.: Shock Tubes. Proceedings of the Seventh International Shock Tube Symposium. University of Toronto Press, Toronto and Buffalo, 1970, pp. 177– 538.
Stalker, R.J.: Isentropic compression of shock tube driver gas. ARS J. 30, 564 (1960).
Stollery, J.L.; Stalker, R.J.: The development and use of free piston wind tunnels. In: R.D. Archer & B.E. Milton (Eds.): Shock Tube and Waves. New South Wales University Press, Sydney, 1983, pp. 41–50.
Stalker, R.J.: Development of a hypervelocity wind tunnel. The Aeronautical Journal 76, 374–384 (1972).
Enkenhus, K.R.: Intermit tend Facilities. VKI Short Course on Advanced Shock Tube Techniques, Febr. 1969.
Wendt, J.F.: European hypersonic wind tunnels. AGARD Conference Proceedings No. 428: Aerodynamics of Hypersonic lifting Vehicles. AGARD-CP-428, Nov. 1987, paper 2.
Bütefisch, K.-A.; Hefer, G.; Hornung, H.; Koppenwallner, G.; Stanewsky, E.: Pflichtenheft für eine Konzeptstudie des geplanten Hochenthalpiewindkanals HEG. DFVLR IB 222–87 A 09, 9. Mai 1987, Göttingen.
Oertel, H.: Stoßrohre, Springer-Verlag, Wien-New York, 1966 p. 670.
Thompson, Ph.A.: Compressible-Fluid Dynamics, McGraw- Hill Book Company, New York, 1972, Section 8.9.
Liepmann, H.W.; Roshko, A.: Elements of Gasdynamics, John Wiley & Sons, New York, 1960, Section 3.2.
Glass, I.I.; Hall, F.G.: Shock Tubes: UTIAS Review No. 12, Part I + II, May 1958.
Van Leer, B.: Towards the ultimate conservative difference scheme. V. A second-order sequel to Godunov’s method. J. Comp. Phys. 32, 101–136 (1979).
Esser, B.; Grönig, H.: Equilibrium shock tube flow of real gases. In: H. Gronig, Ed.: Shock Tubes and Waves. Proceedings of the 16th Int. Symp. on Shock Tubes and Waves. VCH-Verlagsgesellschaft, Weinheim 1988, 663–669.
Vincenti, W.G.; Kruger, Ch.H.: Introduction to Physical Gas Dynamics, Wiley & Sons, New York, 1967, Chapter IV, Sect. 10.
Horton, T.E.: The Computation of Partition Functions and Thermochemistry Data for Atomic, Ionic, Diatomic and Polyatomic Species, JPL Technical Report 32–1425 (1970).
Horton, T.E.; Menard, W.A.: A Program for Computing Shock-Tube Gas-dynamics Properties, JPL Technical Report 32–1350 (1969).
Huber, K.P.; Herzberg, G.: Molecular Spectra and Molecular Structure, IV, Constants of Diatomic Molecules, van Nostrand Reinhold, New York, 1979.
Smoller, J.: Shock Waves and Reaction-Diffusion Equations, Springer, New York, 1983.
Ames Research Staff: Equations, tables and charts for compressible flow. Ames Aeronautical Laboratory, Rep. 1135 (1952).
Mirels, H.: Shock tube testing time limitation due to turbulent-wall boundary layer. AIAA J. 2, 84–93 (1964).
Vyska, K.: Akustische Theorie zur Ermittlung des Einflusses des Rei-bungsdruckabfalles auf den Gaszustand hinter einer reflektierten Stoflwelle in einem Stoflwellenrohr. PhD Thesis, RWTH Aachen, 1969.
Davies, L.; Wilson, J.L.: Influence of reflected shock and boundary layer interaction on shock-tube flows. Phys. Fluids 12, Supp. I, I-37-I-43 (1969).
Mark, H.: The interaction of a reflected shock wave with the boundary layer in a shock tube. NACA TM 1418, March 1958.
Holder, D.W.; Schultz, D.L.: The duration and properties of the flow in a hypersonic shock tunnel. In: F.R. Riddell, Ed: Hypersonic Flow Research, Academic Press, New York, 1962 pp. 513–546.
Stalker, R.J.; Crane, K.C.A.: Driver gas contamination in a high-enthalpy reflected shock tunnel. AIAA J. 16, 277–279 (1978).
Lapworth, K.C., Townsend, J.E.G.: Temperature and pressure studies in the reservoir of a reflected-shock hypersonic tunnel. Nat. Phys. Lab., NPL AERO Rep. 1127, Dec. 1964.
Bull, D.C.; Edwards, D.H.: An investigation of the reflected shock interaction process in a shock tube. AIAA J. 6, 1549–1555 (1968).
Davies, L.; Pennelegion, L.; Gough, P.; Dolman, K.: The effects of high pressure on the flow in the reflected shock tunnel. National Physical Laboratory, NPL AERO REPORT 1072, ARC 25071, Hyp. 349, Sept. 1963.
Kurth, G.: Effects of van der Waals gas driver on shock tube flow. Diploma Thesis, Shock Wave Laboratory, RWTH Aachen, 1988.
Burke, A.F.; Bird, K.D.: The use of conical and contoured expansion nozzles in hypervelocity facilities. CAL Report No. 112, July 1962.
Geiger, R.E.: Short hypersonic contoured nozzles. ARS J. 30, 368–369 (1960).
Baradell, D.L.; Bertram, M.H.: The blunt plate in hypersonic flow. NASA TN D-408, October 1960.
Ritzerfeld, E.: Work in progress in Shock Wave Laboratory, RWTH Aachen (1988).
Lee, J.D.: Axisymmetric nozzles for hypersonic flows. OSU Rept. No. TN (ALOSU) 459–1, WADC TN 59–228, June 1959.
Stalker, R.J.: Shock tunnels for real gas hypersonics. In: Aerodynamics of Hypersonic Lifting Vehicles. AGARD Conference Proceedings No. 428, 1987.
Park, Ch.: Convergence of computation of chemical reacting flows. In: J.N. Moss & C.D. Scott, Eds.: Thermophysical Aspects of Re-entry Flow. AIAA Series Prog, in Astron. and Aeron. Vol. 103, pp. 478–513, (1986).
Bernstein, L.: Tabulated solutions of the equilibrium gas properties behind the incident and reflected normal shock-wave in a shock-tube. I-Nitrogen, II-Oxygen. Ministry of Aviation, Aeronautical Res. Council C.P. No. 626, 1963.
Finke, K.H.: Die zentrierte zweidimensionale Nichtgleichgewichts-Expan-sionsströmung im Hyperschallbereich. Dissertation Aachen, 1970.
Boudreau, A.H.; Adams, J.C. Jr.: Characterization of hypersonic wind tunnel flow fields. AIAA 15th Aerodynamic Testing Conference, May 18–20, 1988.
Hall, T.G.; Treanor, Ch.E.: Nonequilibrium effects in supersonic-nozzle flows. Technical Report, CAL No. 163, March 1968.
Gibson, W.E.; Marrone, P.V.: A similitude for non-equilibrium phenomena in hypersonic flight. AGARDograph 68: High Temperature Aspects of Hypersonic Flow. Pergamon Press, Oxford, 1963, pp. 105–129.
Cox, R.N.; Crabtree, L.F.: Elements of Hypersonic Aerodynamics. The English Universities Press Ltd., London 1965, p. 40.
Hayes, W.D.; Probstein, R.F.: Hypersonic Flow Theory. Academic Press, New York 1959, p. 25.
Koppenwallner, G.: Aerothermodynamik — Ein Schlüssel zu neuen Transport geraten der Luft- und Raumfahrt. Z. Flugwiss. Weltraumforsch. 12, 6–18 (1988).
Probstein, R.F.: Shock wave and flow field development in hypersonic re-entry. ARS J. 31, 185–194 (1961).
Chapman, D.R.; Rubesin, M.W.: Temperature and velocity profiles in the compressible laminar boundary layer with arbitrary distribution of surface temperature. J. Aeron. Sci. 16, 547–565 (1949).
Chevallier, J.P.: Rétrospective sur les moyens d’essais et de mesure en hypersonique. 22ème Colloque d’Aerodynamique Appliqué, Lille 1985.
Müller, H.M; Grönig, H.: Experimental investigations on shock focusing in water. Proc. 12th Int. Congr. on Acoustics Vol. III, H3–3, Toronto 1986.
Bernstein, L.: Force measurement in short-duration hypersonic facilities. AGARDograph No. 214, Nov. 1975, London.
Anonymous: Hypersonic shock tunnel. Description and capabilities. ARVIN/CALSPAN, Dec. 1984.
Schultz, D.L.; Jones, T.V.: Heat transfer measurements in short-duration hypersonic facilities. AGARDograph No. 165, Febr. 1973.
Vidal, R.J.: Model instrumentation techniques for heat transfer and force measurements in a hypersonic shock tunnel. Corn. Aeron. Lab. Rep. AD-917-A1, 1956.
Cook, W.J.; Felderman, E.J.: Reduction of data from thin film and transfer gauges. A concise numerical technique AIAA J. 4, 561–562 (1966).
Merzkirch, W.: Techniques of flow visualization. AGARD AG 302, Dec. 1987.
Miyashiro, S.; Grönig, H.: Low-jitter reliable nanosecond spark source for optical short-duration measurements. Exp. in Fluids 3, 71–75 (1985).
Van der Meer, J.: Kurzzeitmessung der Rotationstemperatur von Stickstoff mit Hilfe der Elektronenstrahlfluoreszenz. Dissertation, RWTH Aachen, 1977.
Schneider, K.-P.; Park, Ch.: Shock tube study of ionization rates of NaCl-contaminated argon. Phys. Fluids 18, 969–981 (1975).
Fritz, K.R.: Zeitaufgeloste massenspektrometrische Untersuchungen der Kinetik schneller homogener Reaktionen hinter reflektierten Stofiwellen. Dissertation RWTH Aachen, 1976.
Thor, H.J.; Gronig, H.: Dynamic measurement of the electron velocity distribution in rarefied weakly ionized argon. Experiments in Fluids 2, 42–46 (1984).
Smith, C.E.: The starting process in a hypersonic nozzle. J. Fluid Mech. 24, 625–640 (1966).
Holden, M.S.: Establishment time of laminar separated flows. AIAA J. 9, 2296–2298 (1978).
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Esser, B., Grönig, H., Olivier, H. (1992). High-Enthalpy Testing in Hypersonic Shock Tunnels. In: Bertin, J.J., Periaux, J., Ballmann, J. (eds) Advances in Hypersonics. Birkhäuser, Boston, MA. https://doi.org/10.1007/978-1-4612-0379-7_5
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DOI: https://doi.org/10.1007/978-1-4612-0379-7_5
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