Accession Number:

AD0871144

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 0.3 Through 1.2

Descriptive Note:

Final rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1970-06-01

Pagination or Media Count:

78.0

Abstract:

Static force tests were conducted on a separable-nose crew escape capsule in the presence of the forward section of an airplane fuselage. The capsule escape rocket exhaust plume was simulated with high-pressure air heated to a total temperature of approximately 100F. Data were obtained at Mach numbers of 0.3, 0.6, 0.9, and 1.2 at capsule angles of attack from -15 to 22 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 with the fuselage at zero-degree angle of attack and zero-degree sideslip. Data were obtained both with and without rocket exhaust plume simulation.

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE