TRANSONIC AERODYNAMIC LOADING CHARACTERISTICS OF A WING-BODY-TAIL COMBINATION HAVING A 52.5 DEGREE SWEPTBACK WING OF ASPECT RATIO 3 WITH CONICAL WING CAMBER AND BODY INDENTATION FOR A DESIGN MACH NUMBER OF THE SQUARE ROOT OF 2
Abstract
A inves iga io as been made of the effects of conical wing camber and body indentation ccordi g to t e supersonic area rule on the aerodynamic wing loading characteristics of a wingbody-tail configuration at transonic speeds. The wing aspect ratio was 3, aper ratio was 0.1, and quarter-chord-line sweepback was 52.5 deg with 3-perc t- ick airfoil sec ions. The tests were conducted in the Langley 16-foot transonic unnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0 to 14 deg with Rey olds numbers based on mean aerodyna ic chord varying from 7 x 10 to the 6th power to 8 x 10 to the 6th power. Conical camber delayed wing-tip stall and r duced s verity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced the transonic chordwise centerof-pressure travel from about 8 percent to 5 percent of the mean aerodyn mic chord. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1961
- Accession Number
- AD0265253
Entities
People
- Marlowe D. Cassetti
- Richard J. Re
- William B. Igoe
Organizations
- National Aeronautics and Space Administration