Effects of two-dimensional sinusoidal waves on heat transfer and pressure over a plate at Mach 8.0
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[1] J. P. Arrington. Heat transfer and pressure distributions due to sinusoidal distortions on a flat plate at Mach 20 in helium , 1968 .
[2] A. M. Cary,et al. Effect of two-dimensional multiple sine-wave protrusions of the pressure and heat-transfer distributions for a flat plate at Mach 6 , 1968 .
[3] J. P. Arrington,et al. Heat transfer to wavy wall in hypersonic flow. , 1967 .
[4] C. L. Jaeck,et al. Analysis of pressure and heat transfer tests on surface roughness elements with laminar and turbulent boundary layers Final report , 1966 .
[5] M. H. Bertram. Hypersonic laminar viscous interaction effects on the aerodynamics of two-dimensional wedge and triangular planform wings , 1966 .
[6] Michael Holden,et al. Experimental studies of separated flows at hypersonic speeds. II - Two-dimensional wedge separated flow studies. , 1966 .
[7] L. R. Jackson,et al. Structural concepts for hydrogen-fueled hypersonic airplanes , 1966 .
[8] P. F. Holloway,et al. An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 , 1965 .
[9] E. Murphy. Heat transfer in the vicinity of a two- dimensional protuberance , 1965 .
[10] P. Stainback. Heat-transfer measurements at a mach number of 8 in the vicinity of a 90 degree interior corner aligned with the free stream velocity , 1964 .
[11] P. F. Holloway,et al. Effect of controlled surface roughness on boundary-layer transition and heat transfer at mach numbers of 4.8 and 6.0 , 1964 .
[12] M. H. Bertram,et al. Effect of Surface Distortions on the Heat Transfer to a Wing at Hypersonic Speeds , 1963 .
[13] S. C. Dixon,et al. TECHNICAL NOTE D- 1626 EXPERIMENTAL PRESSURES AND TURBULENT HEAT-TRANSFER COEFFICIENTS ASSOCIATED WITH SINUSOIDAL PROTUBERANCES ON A FLAT PLATE AT A MACH NUMBER OF 3 , 1963 .
[14] I. K. Collins,et al. Heat-Transfer And Pressure Measurements on a Flat-Plate Surface and Heat-Transfer Measurements on Attached Protuberances in a Supersonic Turbulent Boundary Layer at Mach Numbers Of 2.65, 3.51, and 4.44 , 1962 .
[15] M. H. Bertram,et al. The Blunt Plate In Hypersonic Flow , 1960 .
[16] Dean R. Chapman,et al. Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition , 1958 .
[17] M. H. Bertram. Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9 , 1956 .
[18] Y. S. Touloukian,et al. Tables of thermal properties of gases , 1955 .