Accession Number : ADA130387
Title : Laser Velocimeter Developments for Surveying Thin Boundary Layers in a Mach 6 High Reynolds Number Flow.
Descriptive Note : Final technical rept. Jun-Dec 81,
Corporate Author : AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
Personal Author(s) : O'Heren,Charles H ; Parobek,Daniel M ; Weissman,Clifford B
PDF Url : ADA130387
Report Date : Feb 1983
Pagination or Media Count : 42
Abstract : Two-component fringe-counter type laser velocimeter techniques were developed to measure model boundary layer velocity profiles in a Mach 6 High Reynolds Number Wind Tunnel. Free stream velocities were approximately 3500 feet per second. Boundary layers as thin as 0.20 inches were surveyed to within .007 inches of the surface of a 16 inch wide sharp leading edge flat plate. Optical, signal processing, and computational techniques and equipment are discussed. Artificial flow field seeding of 1.0 to 2.0 micron particles was achieved in the facility stagnation section. This test program was conducted at stagnation pressures of 700 and 1400 psia. The stagnation temperature for the entire program was 1100 degrees R. Data rates of 2,000 per second were realized through the velocimeter test volume.
Descriptors : *Measuring instruments, *Laser velocimeters, *Boundary layer flow, *Hypersonic flow, Test methods, Test equipment, Anemometers, Wind tunnel tests
Subject Categories : Test Facilities, Equipment and Methods
Distribution Statement : APPROVED FOR PUBLIC RELEASE