Accession Number:

ADA070433

Title:

Some Aerodynamic Performance Calculations on Missile Configurations.

Descriptive Note:

Final rept. 15 Jan 77-30 Nov 78,

Corporate Author:

TENNESSEE UNIV SPACE INST TULLAHOMA

Report Date:

1979-05-31

Pagination or Media Count:

80.0

Abstract:

Axisymmetric bodies with a clean configuration have a rather flat pressure distribution on the cylindrical portion of the body. In this report, axisymmetric bodies with surface cut outs are modelled using an inviscid flow approach with experimental flow results. Literature is available on numerical schemes for aerodynamic calculations on fins at moderately high angles of attack. Fin-body combinations are studied using a nose vortex model and some results reported. Also studied is the asymmetric nose vortex problem on an axisymmetric body at higher angles of attack. This has been studied for conical and ogive forebodies using a modified Wardlows method. Author

Subject Categories:

  • Guided Missiles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE