Accession Number:

AD0524161

Title:

An Investigation of External Burning Propulsion for the 75mm Projectile

Descriptive Note:

Final technical rept. 1 Mar-30 Nov 1972

Corporate Author:

ATLANTIC RESEARCH CORP ALEXANDRIA VA

Personal Author(s):

Report Date:

1973-01-01

Pagination or Media Count:

180.0

Abstract:

Twenty external burning combustion tests were conducted with a 75mm half-model using the exhausts from fuel-rich solid propellants as the fuels. Test conditions simulated Mach 2.5 and Mach 2.0 flight at both sea level and an altitude of 15,000 ft. Base pressure ratios up to 0.85 were obtained at sea level, while at altitude these ratios were greater than unity. There was strong evidence that a wind tunnel interference effect severely restricted the measured base pressure rises. Since this interference effect would not be present in a real flight environment, flight performance should be significantly better than indicated by the current results.

Subject Categories:

  • Ammunition and Explosives
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE