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Prediction of Pressure Fluctuations Associated with Maneuvering Reentry Weapons

Author: Anthony L Laganelli; Air Force Wright Aeronautical Laboratories.; Air Force Flight Dynamics Laboratory (U.S.); Science Applications, inc.
Publisher: Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, United States Air Force, 1984.
Series: Air Force Wright Aeronautical Laboratories.; Technical Report
Edition/Format:   Book : National government publication : English
Database:WorldCat
Summary:
An experimental program was conducted at the AEDC von Karman facility, Tunnels A and B, in which acoustic pressure fluctuation data were acquired on a 7 degree half-cone-angle model featuring a control surface. The objective was to define the aeroacoustic environment applicable to re-entry vibration response analysis for both ballistic and maneuvering vehicles. Wind tunnel measurements were obtained at Mach 4 and 8  Read more...
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Details

Material Type: Government publication, National government publication
Document Type: Book
All Authors / Contributors: Anthony L Laganelli; Air Force Wright Aeronautical Laboratories.; Air Force Flight Dynamics Laboratory (U.S.); Science Applications, inc.
OCLC Number: 430340749
Notes: "February 1984."
Research supported by the United States Air Force Wright Aeronautical Laboratories, and performed by Science Applications, Inc.
Description: xiii, 165 p. : ill. ; 28 cm.
Series Title: Air Force Wright Aeronautical Laboratories.; Technical Report
Responsibility: A. L. Laganelli.

Abstract:

An experimental program was conducted at the AEDC von Karman facility, Tunnels A and B, in which acoustic pressure fluctuation data were acquired on a 7 degree half-cone-angle model featuring a control surface. The objective was to define the aeroacoustic environment applicable to re-entry vibration response analysis for both ballistic and maneuvering vehicles. Wind tunnel measurements were obtained at Mach 4 and 8 for several values of freestream Reynolds number and model angle of attack. Stationary zones of laminar, transitional, and turbulent flow over the model were achieved. Acoustic data were reduced to rms fluctuating pressure, and power and cross-power spectral densities. Results were normalized using local boundary layer parameters for comparison with previous high speed measurements. The present study re-examined the aeroacoustic environment prediction capability relative to compressible flow conditions. Moreover, boundary layer characteristic lengths and velocities were reviewed in order to develop normalization procedures required for development of appropriate aeroacoustic scaling laws. It was determined that fluctuating pressure characteristics described by incompressible theory as well as empirical correlations could be modified to a compressible state through a transformation function. In this manner, compressible data were transformed to the incompressible plane where direct use of more tractable prediction techniques are available for engineering design analyses.

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