Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel Page: 3 of 22
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2 NACA RM L52J23a
The purpose of the tests reported in the present paper was to extend
the investigation in the Langley 9-inch supersonic tunnel of the zero-
lift drag components of the NACA RM-10 body alone (ref. 11) to include
the effects of the fins on a 0.050O-scale model, and to determine the lift,
drag, and pitching moment of the finned body over an angle-of-attack
range of 50. The effects upon the aerodynamic characteristics of
varying the ratio of sting-shield diameter to base diameter were also
investigated. The tests were conducted at a Mach number of 1.62 and a
Reynolds number of 2.66 x 106.
SYMBOLS
A maximum cross-section area of body
Az wetted area of body forward of fin-body juncture
AW wetted area of body alone (surface area forward of base)
a angle of attack of model
CL lift coefficient, Lift/qA
CD drag coefficient, Drag/qA
Cm pitching-moment coefficient about the station of maximum body
diameter, Moment/qAL
La da
Cma = dC at CL = O
da
db base diameter
dmax maximum body diameter
ds sting-shield diameter at model base
L length _of body
2 distance from model nose to fin-body juncture
M Mach number.dynamic pressure, pV2/2
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Coletti, Donald E. Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel, report, December 19, 1952; (https://digital.library.unt.edu/ark:/67531/metadc279567/m1/3/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.