Calculations for a Generic Fighter at Supersonic High-Lift Conditions,
Abstract
The parabolized Navier/Stokes 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1986
- Accession Number
- ADP005133
Entities
People
- G. Blom
- H. Yoshihara
- J. C. Wai
Organizations
- Boeing Military Aircraft