THE DESIGN AND TEST AT MACH NUMBER 2.5 OF TWO LOW-WAVE-DRAG RING-WING CONFIGURATIONS OF ASPECT RATIO 1.3 AND 2.6
Abstract
An approximate scheme for the design of ringwing configurations which have almost no supersonic wave drag (at zero angle of attack and design Mach number 2.5) is described. This method is based on the Whitham correction to linearized small-perturbation theory. Windtunnel tests of two configurations designed by this method tend to verify the predicted wavedrag reduction. Discrepancies with the theoretical calculations are due mainly to their assumption of inviscid, isentropic flow. It appears probable that the design method could be improved by allowing for boundary-layer growth and for shock formation. The results of measurements of the lift, drag and pitching moment of the test models at angle of attack are included. All tests were conducted at the design Mach number 2.5. Whenever possible, the measured results are compared with theoretical predictions a d the agreement is generally good. The presence of the horizontal pair of the cruciform struts and the body served to reduce the lifting drag factor of the complete configuration about 10 per cent from that of the ring wing alone. The necessary struts can be designed so that their drag is of the order of 5 per cent of the configuration drag. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1962
- Accession Number
- AD0278486
Entities
People
- Beverly J. Beane
- Daniel T. Nowlan
- Frederick K. Browand
Organizations
- RAND Corporation