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Advanced Supersonic Technology concept AST-100 characteristics developed in a baseline-update studyThe advanced supersonic technology configuration, AST-100, is described. The combination of wing thickness reduction, nacelle recontouring for minimum drag at cruise, and the use of the horizontal tail to produce lift during climb and cruise resulted in an increase in maximum lift-to-drag ratio. Lighter engines and lower fuel weight associated with this resizing result in a six percent reduction in takeoff gross weight. The AST-100 takeoff maximum effective perceived noise at the runway centerline and sideline measurement stations was 114.4 decibels. Since 1.5-decibels tradeoff is available from the approach noise, the required engine noise supression is 4.9 decibels. The AST-100 largest maximum overpressure would occur during transonic climb acceleration when the aircraft was at relatively low altitude. Calculated standard +8 C day range of the AST-100, with a 292 passenger payload, is 7348 km (3968 n.mi). Fuel price is the largest contributor to direct operating cost. However, if the AST-100 were flown subsonically (M = 0.9), direct operating costs would increase approximately 50 percent because of time related costs.
Document ID
19760011967
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Baber, H. T., Jr. (NASA Langley Research Center Hampton, VA, United States)
Swanson, E. E. (Vought Corp. Hampton Tech. Gen., United States)
Date Acquired
September 3, 2013
Publication Date
January 16, 1976
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-72815
Accession Number
76N19055
Funding Number(s)
PROJECT: RTOP 743-04-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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