An Analysis of Measured Sonic-Boom Pressure Signatures From a Langley Wind-Tunnel Model of a Supersonic-Cruise Business Jet Concept

摘要

Pressure signatures generated by the wind-tunnel model of a Business-Jet Concept were measured at a Mach number of 2, at (1ift/cruise lift) ratios of 0.5 and 1.0, and at separation distances of 9.5 and 18 inches. Analysis of the pressure signature data showed the engine-nacelle disturbances were as difficult to "hide" in the flow-field of a 10-passenger supersonic-cruise business jet as they were in the similar part of the flow-field of a 300-passenger supersonic-cruise transport. This result indicated that it was more, not less, difficult to tailor the business-jet concept's geometry for sonic boom overpressures that were half those required of the much larger transport aircraft.