Accession Number:

AD0848311

Title:

Force Tests on a Separable-Nose Crew Escape Capsule in Proximity to the Parent Fuselage with Cold Flow Rocket Plume Simulation at Mach Numbers 2 through 5.

Descriptive Note:

Final rept. 30 Oct 1967-28 Sep 1968

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1969-02-01

Pagination or Media Count:

92.0

Abstract:

Static force tests were conducted on a separable-nose crew escape capsule in the presence of the forward section of the airplane fuselage. The capsule escape rocket jet plume was simulated with air heated to a total temperature of approximately 100F. Data were obtained at Mach numbers from 2 through 5 at capsule angles of attack from -15 to 25 deg and angles of sideslip from 0 to 15 deg for various positions of the capsule relative to the fuselage section. All testing was conducted at a fuselage angle of attack and angle of sideslip of zero. Reynolds number, based on a model length of 18.1 in., ranged from 5,700,000 to 12,300,000. Results are presented showing the effects of the fuselage section on the aerodynamic characteristics of the capsule, with and without simulation of the escape rocket exhaust plume. Author

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE