Accession Number:

AD0619397

Title:

UNSTEADY AERODYNAMICS FOR ADVANCED CONFIGURATIONS. PART 5. UNSTEADY POTENTIAL FLOW AROUND SLENDER BODIES AT ANGLES OF ATTACK

Descriptive Note:

Final rept. for 1 Apr 1963-Sep 1964

Corporate Author:

NORTH AMERICAN AVIATION INC DOWNEY CA SPACE AND INFORMATION SYSTEMS DIV

Personal Author(s):

Report Date:

1965-05-01

Pagination or Media Count:

51.0

Abstract:

In the portion of the study covered in this report, linearized theory is developed for potential flow around a slender body at not too large angles of attack. The solution is obtained by definitizing the flow equation and rigorously satisfying the boundary conditions. This approach is completely different from conventional methods in that it constitutes a process of obtaining an analytic solution to the problem of potential flow by a march from the body toward infinity. The extension of this new theory to the nonlinear case is immediate. Having shown it is possible to not restrict the Mach number, it is expected that the new theory should be applicable to the cases of subsonic, transonic and supersonic speeds as well.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE