Lift/drag ratios and sonic boom intensities of a circular wing

The order of attainable lift/drag ratios of a wing of circular planform with biconvex profile has been estimated based on the linearized supersonic flow theory. For this wing, the ground over pressures due to volume and lift have been computed for different flight Mach numbers, thickness to chord ratios, flight altitudes, and wing loadings. It is noted that the booms due to volume and lift are of comparable magnitude even for high flight altitudes. © 1982, Acoustical Society of America. All rights reserved.