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Wind-tunnel/flight correlation study of aerodynamic characteristics of a large flexible supersonic cruise airplane (XB-701) 2: Extrapolation of wind-tunnel data to full-scale conditionsThe results of calculations necessary to extrapolate performance data on an XB-70-1 wind tunnel model to full scale at Mach numbers from 0.76 to 2.53 are presented. The extrapolation was part of a joint program to evaluate performance prediction techniques for large flexible supersonic airplanes similar to a supersonic transport. The extrapolation procedure included: interpolation of the wind tunnel data at the specific conditions of the flight test points; determination of the drag increments to be applied to the wind tunnel data, such as spillage drag, boundary layer trip drag, and skin friction increments; and estimates of the drag items not represented on the wind tunnel model, such as bypass doors, roughness, protuberances, and leakage drag. In addition, estimates of the effects of flexibility of the airplane were determined.
Document ID
19800007772
Document Type
Technical Publication (TP)
Authors
Peterson, J. B., Jr. (NASA Langley Research Center Hampton, VA, United States)
Mann, M. J. (NASA Langley Research Center Hampton, VA, United States)
Sorrells, R. B., III (NASA Langley Research Center Hampton, VA, United States)
Sawyer, W. C. (NASA Langley Research Center Hampton, VA, United States)
Fuller, D. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1980
Subject Category
AERODYNAMICS
Report/Patent Number
L-12688
NASA-TP-1515
Funding Number(s)
PROJECT: RTOP 505-11-13-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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