Accession Number:

AD0001642

Title:

DEVELOPMENT OF HIGH PERFORMANCE ROTARY WING, TIPMOUNTED PULSE-JET ENGINE COMPONENTS

Descriptive Note:

Quarterly engineering rept. No. 4

Corporate Author:

FAIRCHILD ENGINE AND AIRPLANE CORP COSTA MESA CA FAIRCHILD ELECTROTECHNICS DIV

Personal Author(s):

Report Date:

1952-11-15

Pagination or Media Count:

17.0

Abstract:

A 35 increase in cooling air inlet duct area increased the structural strength of the conical engines. Aluminum proved inadequate for fabrication of the cooling air baffle. The XPJ-49-AH-1 AJ-7.5 inlet valve was tested 38 hrs. without failure. The valve tensiometer was fabricated, and the spring elements were calibrated. A set of lower frequency reeds and a multiple-pointfuel- injection system were designed and fabricated for the 10.0-in.-diam.engine. The thrust performance of 4 cowling configurations was evaluated and the high-speed superiority of the short-lip circular type proven. Three designs of 6.75-in.- diam. development engines, as well as the XPJ-43-AH-1 AJ-9.4 and XPJ-49-AH-1 AJ-7.5 engines, were tested at high tip speeds on the special low-g test stand. The XPJ-43-AH-1 engine was tested to 450 ft.sec. and the smaller engines were tested to 550 ft.sec. The altitude effect on cowling parameters, inlet valve parameters, venturi parameters and tube geometry was investigated.

Subject Categories:

  • Aircraft
  • Numerical Mathematics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE