Sonic Boom Minimization through Air Stream Alteration.
Final rept. Mar 70-Jul 71,
GENERAL APPLIED SCIENCE LABS INC WESTBURY N Y
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The potential of modifying supersonic aircraft sonic boom signatures by means of altering the flow field in the vicinity of the aircraft was investigated theoretically. A specific airplane, the NASA SCAT-15F, was selected as a basis, and a cruise flight condition of Mach 2.7, 62,000 feet was chosen. Signatures were computed using real 1962 atmospheric properties. Finite rise times, reduced overpressures, and reduced shock pressure rises were among the signature improvements investigated. Flow field alteration mechanisms considered included free combustion, boundary layer mass addition, force fields, and laser-generated heat fields. Finally, the concept of a separate penalty aircraft was put forth. This would be an aircraft, presumably carrying no payload, that would fly fly in close proximity so that the sonic booms interfere to the baseline aircraft and relieve the necessity of increasing the baseline aircraft gross weight because of sonic boom alleviation schemes. Author