Computation of Hypersonic Transitional Flows Over Cones Using Gas-Kinetic Scheme Coupled with the Turbulence Model
Author:
Publisher
Springer Nature Singapore
Link
https://link.springer.com/content/pdf/10.1007/978-981-19-2689-1_53
Reference16 articles.
1. Muir J, Trujillo A (1972 January) Experimental investigation of the effects of nose bluntness, free-stream unit Reynolds number, and angle of attack on cone boundary layer transition at a Mach number of 6. In: 10th aerospace sciences meeting, p 216
2. Stetson K (1979 January) Effect of bluntness and angle of attack on boundary layer transition on cones and biconic configurations. In: 17th aerospace sciences meeting, p 269
3. Holden M (1985 January) Experimental studies of the effects of asymmetric transition on the aerothermal characteristics of hypersonic blunted slender cones. In: 23rd aerospace sciences meeting, p 325
4. Schneider SP (2004) Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies. Prog Aerosp Sci 40(1–2):1–50
5. Li X, Fu D, Ma Y (2010) Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack. Phys Fluids 22(2):025105
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