Accession Number:

AD0255893

Title:

SURFACE PRESSURE TESTS ON BLUNT SLAB WINGS SWEPT TO 0, 45, 60, AND 70 DEGREES AT MACH NUMBERS 1.71, 2.5, 4.0, 7.6 AND ANGLES OF ATTACK UP TO 40 DEGREES

Descriptive Note:

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE NAVAL SUPERSONIC LAB

Personal Author(s):

Report Date:

1960-09-01

Pagination or Media Count:

1.0

Abstract:

An experimental investigation of the two-dimensional surface pressures on blunt, swept, slab wings was conducted. The test was undertaken as part of a more general program in which the flow field behind a blunt slab wing at high angles ofATTACK IN SUPERSONIC AND HYPERSONIC FLOW IS BEING STUDIED. The purpose of the present test was to determine experimentally the effects of leading edge blunting and sweep and angle of attack on the surface pressure distribution of a flat plate. Four models having 0, 45, 60, and 70 degrees of leading edge sweep were built, instrumented with 16 to 18 pressure taps and tested at Mach numbers 1.71, 2.5, 4.0, and 7.6 through an angle of attack range of -24 to 40 degrees. Each wing has a 38 inch cylindrical leading edge and flat upper, lower, and base surfaces. Tabulated and graphical presentation of the pressure data is included. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE