Effects of Reynolds number and model support on the supersonic aerodynamic chacteristics of a 140° included-angle cone /
by Charles D. Trescot, Jr., and Clarence A. Brown, Jr., and Dorothy T. Howell.

Description

Main Author

Trescot, Charles D.

Related Names

Howell, Dorothy T.
Brown, Clarence A.
Langley Research Center.

Language(s)

English

Published

Washington, D.C. : National Aeronautics and Space Administration ; 1974.

Subjects

Wind tunnel models.
Reynolds number.
Aerodynamics, Supersonic.
Cone > Cone / Aerodynamics.
Wind tunnel apparatus.
Supersonic speeds.
Reynolds number.
Pressure measurements.
Aerodynamic interference.
Wind tunnel tests.
Static aerodynamic characteristics.
Conical bodies.
Aerodynamic forces.

Summary

An investigation has been made in the Langley Unitary Plan wind tunnel to determine the effects of Reynolds number and sting-support interference on the static aerodynamic characteristics of a 140 deg-included-angle cone. Base pressures and forces and moments of the model were measured at Mach numbers of 1.50, 2.00, 2.94, and 4.00 for ratios of sting diameter to model diameter that varied from 0.125 to 0.500 through an angle-of-attack range from about minus 4 deg to 13 deg. The Reynolds number, based on model diameter 4.80 in. was varied from 161,000 to 415,000.

Note

"NASA TM X-3019."
Performing organization report no.: L-9383.
"July 1974."
Cover title.
Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 9/19/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740020368_1974020368.pdf.

Physical Description

72 p. : ill. ; 27 cm.

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