Abstract
The Caltech T5 reflected shock tunnel is used to produce hypervelocity flow over a range of velocities and pressures by varying the test gas and operating parameters of reservoir enthalpy (hres) and reservoir pressure (Pres). One area of research in T5 is the measurement of boundary layer behavior and transition from laminar to turbulent flow on a smooth 5-degree half-angle cone [3, 1, 11].
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References
Adam, P.H., Hornung, H.G.: Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data. Journal of Spacecraft and Rockets 34(5), 614–619 (1997)
Dorrance, W.H.: Viscous Hypersonic Flow: Theory of Reacting and Hypersonic Boundary Layers. McGraw-Hill (1962)
Germain, P., Hornung, H.G.: Transition on a Slender Cone in Hypervelocity Flow. Experiments in Fluids 22, 183–190 (1997)
Hornung, H.G.: Performance data of the new free-piston shock tunnel at GALCIT. AIAA 92-3943 (1992)
Jewell, J.S., Leyva, I.A., Parziale, N.J., Shepherd, J.E.: Effect of gas injection on transition in hypervelocity boundary layers. In: Proceedings of the 28th International Symposium on Shock Waves, vol. 1, pp. 735–740 (2011)
Jewell, J.S., Shepherd, J.E., Leyva, I.A.: Supplemental data for Shock tunnel operation and correlation of boundary layer transition (2013), http://www2.galcit.caltech.edu/T5/publications/publications.html
Jewell, J.S., Wagnild, R.M., Leyva, I.A., Candler, G.V., Shepherd, J.E.: Transition within a hypervelocity boundary layer on a 5-degree half-angle cone in air/CO2 mixtures. AIAA 2013-0523 (2013)
Leyva, I.A., Jewell, J.S., Laurence, S., Hornung, H.G., Shepherd, J.E.: On the impact of injection schemes on transition in hypersonic boundary layers. AIAA 2009-7204 (2009)
Mack, L.M.: Boundary-layer stability theory. Special Course on Stability and Transition of Laminar Flow. AGARD Report 709 (1984)
Parziale, N.J., Shepherd, J.E., Hornung, H.G.: Reflected shock tunnel noise measurement by focused differential interferometry. AIAA 2012-3261 (2012)
Rasheed, A., Hornung, H.G., Fedorov, A.V., Malmuth, N.D.: Experiments on Passive Hypervelocity Boundary-Layer Control Using an Ultrasonically Absorptive Surface. AIAA Journal 40(3) (2002)
Schneider, S.P.: Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition. Journal of Spacecraft and Rockets 38(3), 323–333 (2001)
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Jewell, J.S., Shepherd, J.E., Leyva, I.A. (2015). Shock Tunnel Operation and Correlation of Boundary Layer Transition on a Cone in Hypervelocity Flow. In: Bonazza, R., Ranjan, D. (eds) 29th International Symposium on Shock Waves 1. ISSW 2013. Springer, Cham. https://doi.org/10.1007/978-3-319-16835-7_116
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DOI: https://doi.org/10.1007/978-3-319-16835-7_116
Publisher Name: Springer, Cham
Print ISBN: 978-3-319-16834-0
Online ISBN: 978-3-319-16835-7
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