TRANSONIC LOADS CHARACTERISTICS OF A 3-PERCENT-THICK 60 DEGREES DELTA-WING-BODY COMBINATION
Abstract
An investigation has been made in the Langley 16-foot transonic tunnel to determine the aerodynamic loading characteristics of a 3-percentthick, aspect-ratio-2.06, 60 degree delta-wingbody combination. The Mach number range was from 0.80 to 1.05 and the average Reynolds number based on wing mean aerodynamic chord was 10 x 10 to the 6th power. The angle-of-attack range was from 0 degrees to 26 degrees but was limited at the highest Mach numbers by tunnel drive power. Pressure distributions, spanwise loadings, integrated wing coefficients, and tabulated pressure coefficients are presented for the range of Mach numbers and angles of attack. The results indicate that a free leadingedge separation vortex is the dominant flowfield phenomenon at all Mach numbers and that, consequently, there are only slight changes in the spanwise loadings with Mach number. There is a slight outboard shift in center of pressure with an increase in Mach number. The chordwise position of the center of pressure varies from 46 to 55 percent of the mean aerodynamic chord when the Mach number is increased from 0.80 to 1.05. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1961
- Accession Number
- AD0256507
Entities
People
- John M. Swihart
- Willard E. Jr. Foss
Organizations
- National Aeronautics and Space Administration