Summary
DLR Lampoldshausen carried out cold flow tests to study the flow field in a truncated ideal contour nozzle at low nozzle pressure ratios. A convex shaped Mach disk was found for nozzle pressure ratios less than 10 and a slight concave one for nozzle pressure ratios more than 20. Due to boundary layer transition the convex Mach disk is temporary tilted and redirects the flow towards the nozzle wall. Accompanying numerical simulations compare well with the experiments.
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References
Ciezki H.: Entwicklung eines Farbschlierenverfahrens unter besonderer Berücksichtigung des Einsatzes an einem Stosswellenrohr, Diploma Thesis, Technical University Aachen, 1985
Cords P.: A High Resolution, High Sensitivity Colour Schlieren Method, S.P.I.E Journal, Vol. 6, 1968
Donaldson C. and Lange R.: Study of the Pressure Rise across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers, NACA RM L52C21, 1952
Frey M.: Behandlung von Strömungsproblemen in Raketendüsen bei Überexpansion, Ph. D. Thesis, Universität Stuttgart, 2001
Frey M. et al.: Joint European Effort Towards Advanced Rocket Thrust Chamber Technology, 6th International Conference on Launcher Technologies, 2005
Kwan W. and Stark R.: Flow Separation Phenomena in Subscale Rocket Nozzles, AIAA Paper 2002-4229, 2002
Lawrence R.: Symmetrical and Unsymmetrical Flow Separation in Supersonic Nozzles, NASA CR 92587, 1967
Mack A. and Hannemann V.: Validation of the Unstructured DLR-TAU-Code for Hypersonic Flows, AIAA Paper 2002-311, 2002
Nasuti F., Onofri M. and Pietropoli E.: Prediction of Shock Generated Vortices in Rocket Nozzles, AIAA Paper 2005-317, 2005
Pilinski C. and Nebbache A.: Flow Separation in a Truncated Ideal Contour Nozzle, Journal of Turbulence, Vol. 20, No. 3, 2004
Schlichting H.: Grenzschicht-Theorie, 9. Auflage, ISBN 3-540-55744-X, 1997
Shapiro A.: The Dynamics and Thermodynamics of Compressible Fluid Flow, Volume 2, ISBN 0-89874-566-7, 1985
Stark R. and Wagner B.: Experimental Flow Investigation of a Truncated Ideal Contour Nozzle, AIAA Paper 2006-5208, 2006
Wagner B., Karl S. and Hannemann K.: Test Case 1a: Short Nozzle Under Separated Flow Condition Numerical Investigation with the DLR Tau-Code, Proceedings of The FSCD-ATAC Workshop, Noordwijk, 15-16th November, The Netherlands, 2006
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© 2009 Springer-Verlag Berlin Heidelberg
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Stark, R., Wagner, B. (2009). Mach disk shape in truncated ideal contour nozzles. In: Hannemann, K., Seiler, F. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-85181-3_28
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DOI: https://doi.org/10.1007/978-3-540-85181-3_28
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-85180-6
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