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Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers up to 1.9Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions. The agreement between theoretical and experimental zero-lift wave-drag coefficients was generally very good, especially for a fuselage or for fuselage-wing combinations that were vertically symmetrical. For other models that had rapid changes in body shape and/or were not vertically symmetrical, the agreement of theory with experiment ranged from fair to poor, depending on the severity of the change in shape.
Document ID
19660010455
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Petersen, R. B. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
March 27, 1957
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-A56I07
Accession Number
66N19744
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
DRAG COEFFICIENT
NOSE CONE
ZERO LIFT
WING BODY
WAVE DRAG
TAIL

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