Performance of Two Types of High Speed, High Efficiency ‎Axisymmetric Intakes

Document Type : Research Paper


1 School of Earth Sciences & Engineering, Tomsk Polytechnic University, 634050, Tomsk, Russia

2 Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences,‎ ‎630090, Novosibirsk, Russia

3 Ryerson University, ON M5B 2K3, Toronto, Canada‎


Performance of two axisymmetric air intakes are compared at conditions suitable for Mach number range from 2 to 8. First is the Busemann intake and second is the reversed isentropic nozzle. The isentropic nozzle is built by the method of characteristics. The contour of this nozzle is taken as a compression surface for the incoming flow. Performances of these two intakes are compared by comparison of both viscous and inviscid CFD calculations at Mach 6. Viscous flow calculations show that the total pressure recovery in compression section is 0.8316 in the Busemann intake and 0.869 in the reversed isentropic nozzle intake.


Main Subjects

[1] Van Wie, D.M., Scramjet Intakes: Scramjet Propulsion, AIAA, 2001.
[2] Van Wie, D.M., Molder, S., Application of Busemann Intake Designs for Flight at Hypersonic Speeds, Aerospace Design Conference, Irvine, CA, AIAA Paper, 92-1210, 1992.
[3] Ogawa, H., Mölder, S., Boyce, R., Effects of Leading-Edge Truncation and Stunting on Drag and Efficiency of Busemann Intakes for Axisymmetric Scramjet Engines, Journal of Fluid Science and Technology, 8(2), 2013, 186-199.
[4] Timofeev, E.V., Tahir, R.B., Molder, S., On Recent Developments Related to Flow Starting in Hypersonic Air Intakes, 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, OH, AIAA, 2008-2512, 2008.
[5] Molder, S., The Busemann Air Intake for Hypersonic Speeds: Hypersonic vehicles - past, present and future developments, IntechOpen, 2018.
[6] Busemann, A., Die Achsensymmetrische Kegelige Überschallströmung, Luftfahrtforschung, 19, 1942, 137-144.
[7] Flock, A.K., Guelhan, A., Viscous Effects and Truncation Effects in Axisymmetric Busemann Scramjet Intakes, AIAA Journal, 54(6), 2016, 1881-1891.
[8] Kraiko, A.N., Tillyaeva, N.I., Axisymmetric-conical and Locally Conical Flows Without Swirling, Journal of Applied Mechanics and Technical Physics, 55(2), 2014, 282–298.
[9] Blokhin, A.M., Vetlutskaya, L.M., Gutov, B.I., Dolgov, V.N., Zatoloka, V.V., Shumsky, V.V., Convergent Input Diffusers and Axisymmetric Supersonic Conical Buzemann Flows, Aerophysical Research, ITAM SB RAS, 1972, 105−108. (In Russian)
[10] Gutov, B.I., Zatoloka, V.V., Convergent Input Diffusers with an Initial Shock Wave and Additional External Compression, Aerophysical Research, ITAM SB RAS, 1973, 64−66. (In Russian)
[11] Gutov, B.I., Zatoloka, V.V., Hypersonic Axisymmetric Compression Flows in Channels Without a Central Body, Issues of Gas Dynamics, ITAM SB RAS , 1975, 213−216. (In Russian)
[12] Gounko, Yu.P., Mazhul, I.I., Numerical Modeling of the Conditions for Realization of Flow Regimes in Supersonic Axisymmetric Conical Inlets of Internal Compression, Thermophysics and Aeromechanics, 22(5), 2015, 545–558.
[13] Gounko, Yu.P., Mazhul, I.I., Design of Supersonic Three-dimensional Inlets Using Two-dimensional Isentropic Compression Flow, Thermophysics and Aeromechanics, 18(1), 2011, 87–100.
[14] Zvegintsev, V., Safonov V., Research of Characteristics of Isentropic Air Intake and Ducted Isentropic Air Intake, Frontiers in Aerospace Engineering, 4(2), 2015, 49-55.
[15] Galkin V.M., Zvegintsev, V.I., Forming of Ducted Axisymmetric Supersonic Air Intakes, Bulletin of the Tomsk Polytechnic University, 326(4), 2015, 117-124.
[16] Galkin, V.M., Vnuchkov, D.A., Zvegintsev, V.I., Gas-dynamic Design of an Axisymmetric Tunnel Air Inlet with Isentropic Compression, Journal of Applied Mechanics and Technical Physics, 56(5), 2015, 111−118.
[17] Galkin, V.M., Zvegintsev, V.I., Vnuchkov, D.A., Investigation of Annular Supersonic Intakes with Isentropic Compression, Thermophysics and Aeromechanics, 23(5), 2016, 645-655.
[18] Braguntsov, E.Ya., Vnuchkov, D.A., Galkin, V.M., Ivanov, I.V., Zvegintsev, V.I., Test of the Annular Supersonic Air Intake with Isentropic Compression in the Wind Tunnel, Tomsk State University Journal of Mathematics and Mechanics, 43(5), 2016, 43−52.
[19] Taylor, G.I., Maccoll, J.W., The Air-pressure on a Cone Moving at High Speeds, Proceedings of the Royal Society of London. Series A, Mathematical and Physical Sciences, 139, 1933, 278-311.
[20] Duncan, W., Tables of Supersonic Flow Around Yawing Cones, Nature, 162, 1948, 432-432.
[21] Molder, S., Szpiro, E.J., Busemann Intake for Hypersonic Speeds, Journal of Spacecraft and Rockets, 3(8), 1966, 1303-1304.
[22] Molder, S., A Benchmark for Internal Flow CFD Code, Computational Fluid Dynamics Journal, 12(2), 2003, 408-414.
[23] Anderson, J.D., Modern Compressible Flow with Historical Perspective, McGraw-Hill, Boston, 1990.
[24] Katskova, O.N., Calculation of Equilibrium Flow within Supersonic Nozzles, Computing Centre of RAS, Moscow, 1964. (In Russian)
[25] Rao, G.V.R., Exhaust nozzle Contour for Optimum Thrust, Jet Propulsion, 28(6), 1958, 377-382.
[26] Ferri A., Elements of Aerodynamics of Supersonic Flows, The MacMillan Co., New York, 1949.
[27] Miele A., Theory of Optimum Aerodynamic Shapes, Academic Press, New York, 1965.