Accession Number:

AD0322238

Title:

HYPERSONIC FLUTTER ANALYSIS OF A DELTA WING AT INITIAL ANGLES OF ATTACK (U)

Descriptive Note:

Corporate Author:

COMPUTER ENGINEERING ASSOCIATES INC PASADENA CA

Personal Author(s):

Report Date:

1960-10-01

Pagination or Media Count:

1.0

Abstract:

A theoretical investigation is made of the flutter of a highly swept delta wing at hypersonic Mach numbers with an initial angle of attack. All calculations assume a local impact theory with no aerodynamic lag or interaction between areas on the surface. A universal flutter curve is found which applies to all similar wings over the Mach number and angle of attack range where these assumptions are valid. Several methods of calculating the aerodynamic coefficients are discussed. Flutter results of both analog solutions and modal analysis are given in terms of dimensionless variables. Analog computations were made on Computer Engineering Associates Direct Analog Computer. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE