Summary
The problem of the intake of air is treated for a missile flying at supersonic speeds, and of changing the kinetic energy of the air into pressure with the least possible losses. Then calculations are carried out concerning the results which can be attained. After a discussion of several preliminary experiments, the practical solution of the problem at hand is indicated by model experiments. The results proved very satisfactory in view of the results which had been attained previously and the values which were anticipated theoretically.
Reprinted from NACA TM No. 1140, June 1947, with permission.
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References
Eggink: Strömungsaufbau und Druckrückgewinn in Überschallkanälen. (Flow Structure and Pressure Recovery in Supersonic Channels.) ZWB-Forschungsbericht No. 1756.
F. Schubert: Zur Theorie des stationären Verdichtungsstoßes. (On the Theory of the Stationary Compression Shock.) Z.A.M.M., vol. 23, no. 3, p. 132, June 1943.
A. Naumann: Wirkungsgrad von Diffusoren bei hohen Unterschallgeschwindigkeiten. (Efficiency of Diffusers at High Subsonic Velocities.) ZWB-Forschungsbericht No. 1705.
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© 1980 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH Braunschweig
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Oswatitsch, K. (1980). Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds (The Efficiency of Shock Diffusers). In: Schneider, W., Platzer, M. (eds) Contributions to the Development of Gasdynamics. Vieweg+Teubner Verlag. https://doi.org/10.1007/978-3-322-91082-0_18
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DOI: https://doi.org/10.1007/978-3-322-91082-0_18
Publisher Name: Vieweg+Teubner Verlag
Print ISBN: 978-3-528-08452-3
Online ISBN: 978-3-322-91082-0
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