Accession Number:

ADP005133

Title:

Calculations for a Generic Fighter at Supersonic High-Lift Conditions,

Descriptive Note:

Corporate Author:

BOEING MILITARY AIRPLANE CO SEATTLE WA

Personal Author(s):

Report Date:

1986-11-01

Pagination or Media Count:

8.0

Abstract:

The parabolized NavierStokes method was used to calculate the flow over a generic fighter configuration with a canard and underwing nacelles at supersonic high lift conditions. The calculated pressure distributions agreed closely with experiments, but the pitot pressure profile predictions for the boundary layer were less satisfactory largely due to an inadequate mesh in the viscous sublayer.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE