Abstract
ABSTRACTIn this study, a series of numerical experiments are performed on supersonic/hypersonic flows over an adiabatic flat plate with transitionally and fully rough surfaces. The Mach numbers simulated are 4, 5, 6, and 7; the flight heights considered are 20, 24, 28, 32, and 36 km. First, a modified roughness correction is proposed and validated with the measured data for low-speed flat-plate cases. It is verified that for the equivalent sand grain heights in the intermediate and fully rough regimes, there is a good agreement with the semi-empirical formula available in the open literature. Then, this roughness correction is applied to high-speed flow regime to investigate the effects of flight heights and Mach numbers on drag for rough-wall flat-plate cases. It is found that within the roughness measured in real flight, the roughness height change has little effect on drag compared to the variations of both flight heights and Mach numbers. The drag coefficient derivation between rough-wall and smooth-wall conditions, achieves the maximum value of 0.79% for the 60 cases selected.
Publisher
Cambridge University Press (CUP)
Reference45 articles.
1. Rough Wall Modification of Two-Layer k−ε
2. Dassler P. , Kozŭlović D. and Fiala A. Modelling of roughness-induced transition using local variables, 5th European Conference on CFD, ECCOMAS CFD, Lisbon, Portugal, June 2010, 14–17.
3. Roughness Corrections for the k–ω Shear Stress Transport Model: Status and Proposals
4. Coleman H. , Hodge B. and Taylor R. Generalized Roughness Effects on Turbulent Boundary Layer Heat Transfer—A Discrete Element Predictive Approach for Turbulent Flow Over Rough Surfaces, Mississippi State University, Mississippi State Engineering and Industrial Research Station, 1983.
Cited by
4 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献