The results of an experimental program carried out in the NASA-Langley 4 x 4 ft supersonic pressure tunnel to investigate the validity of the heat-field concept for sonic-boom alleviation are reported herein. The basic idea of the heat-field concept is to heat the flow about a supersonic aircraft in such a manner as to obtain an increase in effective aircraft shape (area distribution) that will result in a shock-free pressure signature on the ground. In the program, pressure signatures were measured below a series of wind-tunnel models to provide a step-by-step verification of the concept. For the key model tested, nitrogen is passed through the near of an off-axis slender fin situated below a representative SST configuration having its lift equivalence in volume. Comparisons of pressure signatures for this model with no flow, cold flow, and heated flow through the fin demonstrated substantial effects due to flow and due to heat, essentially verifying the use of mass flow and heat fields for providing equivalent area in supersonic flow. In addition, the ability of an off-axis slender fin to produce a finite-rise-time signature in the presence of lift was demonstrated by testing a wing-body model both with and without a solid fin.
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