Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10 Page: 4 of 37
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NACA RM A53D02 3
CN normal force coefficient, normal force
M free-stream Mach number
Pb base pressure, lb/sq ft
q free-stream dynamic pressure, lb/sq ft
R Reynolds number based on free-stream properties and model
RT transition Reynolds number based on free-stream properties and
length of run of the laminar boundary layer
t time, see
a, angle of attack, radians
a mean angle of attack, , radians
1, 2; intervals of time or distance between stations 1 and 2, 1 and
1,s; 3, 2 and 3, etc.
TEST TECHNIQUE AND CONDITIONS
The investigation was conducted in the Ames supersonic free-flight
wind tunnel. In this facility the model is launched from a gun mounted
in the wind-tunnel diffuser and flies upstream through the test section.
Mach numbers below approximately 4 are obtained by firing the model
through still air. Higher Mach numbers are obtained by firing through
the supersonic air stream of the wind tunnel. A detailed discussion of
the test technique will be found in reference 1.
The model tested is shown in figure 1(a). The body has an ogive
nose tangent to a circular-cylindrical afterbody. The fineness ratio of
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James, Carlton S. & Carros, Robert J. Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10, report, June 11, 1953; (digital.library.unt.edu/ark:/67531/metadc59730/m1/4/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.