A study of the application of heat or force fields to the sonic-boom-minimization problem
David S. Miller, Harry W. Carlson, United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1969 - Science - 17 pages
Sonic boom minimization by application of heat or force fields to airplane airflow.
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18.6 kilometers Aerodynamics airplane configuration airplane lengths ahead airplane nose alter the airplane APPLICATION OF HEAT Body length changes in Mach Circular symbols denote differential equations distribution effective cross-sectional electrostatic forces eliminate the shock-wave example of figure finite rise finite rise-time signatures flow field forward and rearward free-stream ground overpressure Ground pressure Heat field heat or force heat-addition influence coefficients information concerning sonic-boom kilometers 61 000 Langley Research Center meters NACA NASA TN number and altitude Performing Organization phantom phantom-body area development phantom-body capture area phantom-body concept phantom-body cross-sectional area phantom-body flow properties phantom-body length phantom-body shape phantom-body surface Pmax practical application practically eliminate pressure coefficient pressure signature requirements with changes selected for cruise shock-wave noise shocks shown in figure signature characteristics simplifying assumptions sonic sonic-boom characteristics sonic-boom problem sonic-boom signature stagnation temperature steady level flight stream tube streamline boundaries supersonic flight total power requirements