Accession Number : AD0255711

Title :   INVESTIGATION AT TRANSONIC SPEEDS OF THE LOADING OVER A 45 DEGREE SWEPTBACK WING HAVING AN ASPECT RATIO OF 3, A TAPER RATIO OF 0.2, AND NACA 65A004 AIRFOIL SECTIONS

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : RUNCKEL,JACK F. ; LEE,EDWIN E. JR.

Report Date : MAY 1961

Pagination or Media Count : 1

Abstract : An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author)

Descriptors :   *SWEPTBACK WINGS, *SWEPT WINGS, *TRANSONIC CHARACTERISTICS, AERODYNAMIC CHARACTERISTICS, AERODYNAMIC CONFIGURATIONS, AIRFOILS, ASPECT RATIO, LOAD DISTRIBUTION, MODEL TESTS, MOMENTS, PRESSURE, REYNOLDS NUMBER, STABILITY, WINGS

Distribution Statement : APPROVED FOR PUBLIC RELEASE