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Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.87 to 1.39 of 1/10-Scale Models of the Northrop MX-775A MissileA flight investigation was made at high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/10-scale model of the Northrop MX-775A missile and a scale model of the missile fuselage. The model of the complete configuration has a 45deg swept wing of aspect ratio 5.5 and a 33deg swept vertical fin. The body model was stabilized by three 45deg swept fins. The-drag-rise Mach number for the model of the complete configuration was approximately 0.96. The drag coefficient based on total wing area was 0.0330 at Mach number 1.39. The drag coefficient of the body model less fin drag was approximately 55 percent that of the complete model at the same Mach number. Addition of the wing to the fuselage apparently resulted in a favorable drag interference near Mach number 1.0.
Document ID
20050030052
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Gillespie, Warren, Jr. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Arbic, Richard G. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
November 7, 1951
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-SL51K07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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