EXPERIMENTAL INVESTIGATION OF FLOW PAST PLANE DELTA WINGS AT M = 5 AND ANGLES OF ATTACK RANGING FROM 0 TO 70 DEGREES,
Abstract
Presented here are the results of an experimental investigation of flow past delta wings with sharp and blunt leading edges and sweep angles of = 60, 70 and 80 degrees at a free-stream Mach number of 5 and angles of attack ranging from 0. t0 70 degrees. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 03, 1968
- Accession Number
- AD0675349
Entities
People
- V. A. Bashkin
Organizations
- Johns Hopkins University Applied Physics Laboratory