HEAT-TRANSFER AND PRESSURE DISTRIBUTIONS ON SPHERICALLY BLUNTED 25' HALF-ANGLE CONE AT MACH

[1]  J. E. Harris Aerodynamic characteristics of a spherically blunted 25 deg cone at a Mach number of 20 , 1967 .

[2]  C. Lewis,et al.  A spherically blunted cone at angle of attack. , 1966 .

[3]  D. W. Eastman,et al.  Flow Fields about Highly Yawed Cones by the Inverse Method , 1965 .

[4]  Edward F. Blick,et al.  Cone pressure distribution at large and small angles of attack , 1964 .

[5]  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 .

[6]  L. Pasiuk COMPARISONS OF EXPERIMENTAL AND THEORETICAL HEAT TRANSFER TO A YAWED SPHERE-CONE MODEL AT SUPERSONIC SPEEDS , 1963 .

[7]  D. Peckham Experiments at hypersonic speeds on circular cones at incidence , 1963 .

[8]  C. Wittliff Heat Transfer to Slender Cones in Hypersonic Air Flow, Including Effects of Yaw and Nose Bluntness , 1962 .

[9]  J. P. Rhudy,et al.  INVESTIGATION OF HYPERSONIC FLOW OVER BLUNTED PLATES AND CONE , 1960 .

[10]  Eli Reshotko,et al.  Heat transfer at the forward stagnation point of blunt bodies , 1955 .

[11]  J Aiaa,et al.  Inviscid Flowfield about a Pointed Cone at an Angle of Attack , 1967 .

[12]  Joseph L. Sims,et al.  Tables for supersonic flow around right circular cones at zero angle of attack , 1964 .

[13]  P. Stainback Heat-Transfer Measurements at a Mach Number of 4.95 on Two 60 deg Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 deg and 45 deg , 1961 .

[14]  I. E. Beckwith,et al.  Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers , 1961 .