Accession Number:

ADA031788

Title:

Investigation of a Ramjet Using Boundary Layer Bleed in a Two-Dimensional Short Curved Wall Subsonic Diffuser.

Descriptive Note:

Final rept. 1 Aug 75-30 Jun 76,

Corporate Author:

GEORGIA INST OF TECH ATLANTA SCHOOL OF ELECTRICAL ENGINEERING

Report Date:

1976-07-01

Pagination or Media Count:

48.0

Abstract:

This report describes the bleeding requirements of a short contoured wall diffuser and the net performance gain of a ramjet equipped with such a high performance subsonic diffuser in terms of Thrust Coefficient and Range versus ramjet with conventional short diffuser. Analysis shows that at cruising Mach number of 2.5, the ramjet may gain 5 in Range and at take-over Mach number of 2.1, the ramjet may gain 6 in Thrust Coefficient. Comparison was also made with other types of high performance subsonic diffusers. In establishing the bleed requirements, detail information was included to show the methods of computing the boundary layer development along the curved wall and over the parallel walls. The latter is of three-dimensional nature which required a method using cone-segment simulation. Author

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE