Estimation of Critical Speeds of Airfoils and Streamline Bodies
Abstract
Methods and charts are presented for estimating the critical compressibility speeds of a large number of airfoils and streamline bodies. A method introduced to allow for the combination of these parts permits the estimation of the critical speed of an airplane wing including the effects of fuselage and nacelles. The systematic effects of thickness, thickness distribution, camber, camber location, leading-edge radius, and lift coefficient are considered. The results indicate that with a given lift coefficient the thickness of the airfoil or of the body is the primary factor controlling its critical speed. For high values of critical speed, the location of maximum thickness and maximum camber should be near the 50-percent-chord point. An airfoil should be designed to have a high value of the critical speed for the lift coefficient at which high-speed operation will occur.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1940
- Accession Number
- ADB807282
Entities
People
- R. G. Robinson
- Ray H. Wright
Organizations
- National Advisory Committee for Aeronautics