Accession Number:

AD0739869

Title:

Reduction of Hypervelocity Heating with Elliptical Leading Edges.

Descriptive Note:

Research rept.,

Corporate Author:

GRUMMAN AEROSPACE CORP BETHPAGE N Y RESEARCH DEPT

Personal Author(s):

Report Date:

1972-02-01

Pagination or Media Count:

32.0

Abstract:

Elliptical shapes are considered for use on wing and fin leading edges and fuselage chines in hypervelocity flight. Calculated distirbutions of heating rates and radiation equilibrium temperatures are presented for a family of ellipses at 0 and 60-degree angles of attack. Heating rates were obtained with a finite difference solution to the laminar compressible boundary layer equations combined with an empirically derived inviscid pressure law for two dimensional flow around elliptical cylinders. Reduction of peak heating rates from circular values is shown up to 17 percent with a blunt ellipse of axis ratio 0.6 at zero angle of attack, and 14 percent with a sharp ellipse of axis ratio 1.6 at 60-degree angle of attack for the re-entry condition studied. This represents a 140 degrees R drop in the radiation equilibrium wall temperature with 0.8 emissivity for zero attack angle, and 100 degrees R drop for 60-degree angle. The calculated temperature distributions are also used to find shapes having minimum surface area requiring protection above certain temperatures. Author

Subject Categories:

  • Guided Missile Reentry Vehicles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE