Accession Number : AD0255716

Title :   TRANSONIC AERODYNAMIC CHARACTERISTICS OF A WINGBODY COMBINATION HAVING A 52.5 DEGREE SWEPTBACK WING OF ASPECT RATIO 3 WITH CONICAL CAMBER AND DESIGNED FOR A MACH NUMBER OF 1.1416

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : IGOE,WILLIAM B. ; RE,RICHARD J. ; CASSETTI,MARLOWE D.

Report Date : MAY 1961

Pagination or Media Count : 1

Abstract : An investigation was made of the effects of conical wing camber and supersonic body indentation on the aerodynamic characteristics of a wing-body configuration at transonic speeds. Wing aspect ratio was 3.0, taper ratio was 0.1, and quarterchord line sweepback was 52.5 with airfoil sections of 0.03 thickness ratio. The tests were conducted in the Langley 16-foot transonic tunnel at various Mach numbers from 0.80 to 1.05 at angles of attack from -4 to 14. The camberedwing configuration achieved higher lift-drag ratios than a similar plane-wing configuration. The camber also reduced the effects of wing-tip flow separation on the aerodynamic characteristics. In general, no stability or trim changes below wing-tip flow separation resulted from the use of camber. The use of supersonic body indentation improved the lift-drag ratios at Mach numbers from 0.96 to 1.05. (Author)

Descriptors :   *WING BODY CONFIGURATIONS, AERODYNAMIC CHARACTERISTICS, AERODYNAMIC CONFIGURATIONS, AIRFOILS, DRAG, JET AIRCRAFT, LIFT, MODEL TESTS, MOMENTS, STABILITY, SUPERSONIC FLOW, SUPERSONIC AIRCRAFT, TRANSONIC CHARACTERISTICS, WINGS

Distribution Statement : APPROVED FOR PUBLIC RELEASE