Accession Number:

AD0646000

Title:

FLUTTER MODEL TEST REPORT

Descriptive Note:

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH ADVANCED TECHNOLOGY PROGRAMS DEPT

Personal Author(s):

Report Date:

1966-06-01

Pagination or Media Count:

21.0

Abstract:

The report covers the wind-tunnel testing, in the flutter regime of a dynamically similar model of the XV-5A Lift-Fan Research Aircraft. The test was restricted entirely to an investigation of the wing-fuselage combination and as such no empennage was represented. Test objectives were slanted toward verification of previous analytical investigations with close attention paid to uncovering any transonic effects which might have been crudely represented analytically. The tests were completed to the point of achieving a 5 percent margin on equivalent speed for the highest aileron rotational frequency studied, approximately 18.9 cps. One actual case of flutter occurred, at M 0.75 and at a dynamic pressure q of approximately 600 psf for an aileron rotational frequency of 14.9 cps. A second case of flutter occurred at M 0.75 and a q greater than 600 psf for an aileron rotational frequency of 16.1 cps however, this latter case of flutter was not considered valid due to the apparent fatiguing of an aileron spring bracket, resulting in essentially a free-floating surface.

Subject Categories:

  • VSTOL
  • Research and Experimental Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE