EXPERIMENTAL-STUDY OF SUPERSONIC TURBULENT-FLOW ON A BLUNTED AXISYMMETRICAL BODY

Surface pressure distribution and turbulent boundary-layer velocity profiles have been measured on a tangentogive cylinder model at small angles of attack (0-4. 5 deg) in a high Reynolds number, Mach 3 airflow. The model wall temperature was approximately adiabatic. The measurements were made using pointed, tangent-hemisphere, and flat-faced nose tips. The effects of tip blunting on the wind- and lee-side velocity profiles, integral thicknesses, shape factor, power law exponent, skin-friction coefficient, and wake strength parameter are presented. It is shown that the results obtained using different geometry tips can be correlated using bluntness length scale obtained by integration of the local tip surface angle from the stagnation point to the point corresponding to shock detachment.