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Aerodynamic Characteristics of NACA RM-10 Missile in 8- by 6-foot Supersonic Wind Tunnel at Mach Numbers from 1.49 to 1.98 II : Presentation and Analysis of Force MeasurementsExperimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
Document ID
19930086134
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Esenwein, Fred T
Obery, Leonard J
Schueller, Carl F
Date Acquired
August 16, 2013
Publication Date
July 21, 1950
Report/Patent Number
NACA-RM-E50D28
Accession Number
93R15424
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
TAIL-BODY COMBINATIONS - MISSILES
FLOW, SUPERSONIC
BODIES - AERODYNAMIC THEORY
LOADS - FUSELAGE, NACELLES, AND CANOPIES

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