Accession Number:

AD0632517

Title:

TURBULENCE STUDY OF A TRANSONIC WIND TUNNEL AND AN ANALYSIS AND TESTS OF AIRCRAFT RESPONSE TO TURBULENCE.

Descriptive Note:

Final rept.

Corporate Author:

NORTH AMERICAN AVIATION INC COLUMBUS OHIO

Personal Author(s):

Report Date:

1964-10-01

Pagination or Media Count:

223.0

Abstract:

A theoretical technique is demonstrated for predicting the random response of a lifting surface on an aircraft traveling at high subsonic speeds through turbulent air. In addition, an evaluation is made of the suitability of a wind tunnel for buffet testing. The theoretical technique is verified by comparing theoretical and experimental values for the frequency response of the horizontal tail of an aeroelastically scaled model. The experimental frequency response was obtained from measurements of the random accelerations and the velocities of exciting turbulence. A theoretical investigation of the effects of structural damping is included. A seven by ten foot transonic wind tunnel is evaluated by presenting power spectral densities, probability densities, intensities and peak factors for the downwash and streamwise components of background turbulence. This turbulence data was measured with a hot-wire anemometer at several spatial locations in the test section and over the operating range. The evaluation is aided by comparing model tests with flight tests. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE