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: 2 of 37
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TECH LIBRARY KAFB, NM
NACA RM A53Do2 0143334
NATIONAL ADIVISORY COMMITTEE FOR AERONAUTICS
EXPERIMENTAL INVESTIGATION OF THE ZERO-LIFT DRAG
OF A FIN-STABILIZED BODY OF FINENESS RATIO 10
AT MACE NUMBERS BETWEEN 0.6 AND 10
By Carlton S. James and Robert J. Carros
Free-flight measurements were made of the zero-lift drag of a
cruciform-finned body at Mach numbers between 0.6 and 10. Reynolds
numbers varied between 0.9 million and 16 million. It was observed that
the drag coefficient after increasing sharply through Mach number 1 drops
rapidly in the low supersonic region to values well below the subcritical
value. The drag coefficients at Mach numbers above 5 were less than half
the M = 0.6 value, and the variation of drag coefficient with Mach number
was considerably less at Mach numbers above 5 than at Mach numbers
The zero-lift drag of this model was predicted over the range of
Mach numbers from 1.5 to 10 and compared with the experimental results.
At Mach number 5 a maximum disagreement between theory and experiment
of 18 percent occurred0 Above and below this Mach number the agreement
improved so that over most of the Mach number range it was within 8 percent.
Accuracy of the prediction was affected principally by uncertainties in
the base drag estimate at low Mach numbers and in the location of
boundary-layer transition at all Mach numbers.
The effect of Reynolds number on the drag was measured at two Mach
numbers, 4.7 and 7.2, and was found to be small. The ranges of Reynolds
numbers covered were between 4 million and 9 million at M = 4.7 and
between 7 million and 16 million at M = 7.2.
An indication was obtained from preliminary data that the effect
on total drag of varying the fin leading-edge profile is small if extreme
bluntness is avoided.
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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/m1/2/: accessed November 15, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.