Accession Number : AD0261196

Title :   TRANSITION OF THE LAMINAR BOUNDARY LAYER ON A DELTA WING WITH 74 DEGREE SWEEP IN FREE FLIGHT AT MACH NUMBERS FROM 2.8 TO 5.3

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : CHAPMAN,GARY T.

Report Date : AUG 1961

Pagination or Media Count : 1

Abstract : The test were conducted at Mach numbers from 2.8 to 5.3, with model surface temperatures small compared to boundary-layer recovery temperature. The effects of Mach number, unit Reynolds number, leading-edge diameter, temperature ratio,AND ANGLE OF ATTACK WERE INVESTIGATED IN AN EXPLORATORY FASHION. The results were compared to results of wind-tunnel tests of swept wings and to results f free-flight tests for unswept leading edges. (Author)

Descriptors :   *DELTA WINGS, *LAMINAR BOUNDARY LAYER, *TRANSITION TEMPERATURE, MACH NUMBER, REYNOLDS NUMBER, SWEPT WINGS, WIND TUNNEL MODELS, WIND TUNNELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE