EXPERIMENTAL INVESTIGATION OF FAR WAKES BEHIND 2 DIMENSIONAL SLENDER BODIES AT M FREESTREAM = 6

An experimental investigation has been conducted at M∞ = 6 to determine mean flow properties for far wakes behind several two-dimensional slender bodies at zero angle of attack. The adiabatic wall configurations tested included a flat-plate model and two 20° wedge models which differed by a factor of two in base height. The effect of wall temperature was examined by cooling the larger wedge model to a temperature of about two tenths of the freestream stagnation temperature. Freestream Reynolds numbers were varied from 50,000 to 200,000 per in. for each of these four configurations. Profile measurements of total temperature and Pitot pressure were combined with centerline static pressures to determine completely the far- wake flowfield from the wake neck downstream to the linear far wake. The effect of transition on mean flow properties was determined. Comparison of laminar wake data for adiabatic wall models with linear wake theory was favorable. Maximum centerline pressures in the far wake for all configurations were generally 10% higher than the freestream pressure. For the cold wall wedge the maximum centerline enthalpy for all cases occurred two base heights downstream of the model base and was triple the magnitude of the freestream enthalpy. The decay rate of enthalpy was “small” when the far wake was laminar. © 1969 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.