Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Aspect Ratios of 1.5 and 2.7 as determined by Flight Tests at Supersonic Speeds
Abstract
Data was obtained by tracking rocket-propelled bodies carrying wings of various plan forms. Results showed that for investigations in Mach number range of 1.05 - 1.35, an increasing swept-back angle and decreasing aspect ratio reduced the value of wing drag coefficient. Decreasing the aspect ratio always decreased the wing drag coefficient; although, this effect was observed to become very small at higher swept-back angles.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 24, 1947
- Accession Number
- ADA801409
Entities
People
- Ellis Katz
- Sidney R. Alexander
Organizations
- National Advisory Committee for Aeronautics