Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds With That Calculated by the Relaxation Method
Abstract
Pressure-distribution measurements were made on a 5-inch-chord NACA 0012 airfoil at zero angle of attack in the Langley rectangular high-speed tunnel, a 4 by 18-inch closed-throat tunnel, and compared with results calculated by Emmons for an equivalent airfoil-channel configuration by using the relaxation method. The comparison shows good agreement between theory and experiment at low Mach numbers. At higher Mach numbers, however, the theoretical calculations indicate higher negative pressure coefficients than were obtained experimentally. The spread between the values predicted by theory and experiment increases with increasing Mach number.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1950
- Accession Number
- ADA380532
Entities
People
- James L. Amick
Organizations
- National Aeronautics and Space Administration