The Effect of Rate of Change of Angle of Attack on the Maximum Lift Coefficient of a Pursuit Airplane
Abstract
The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing has been investigated in stalls of varying abruptness over the Mach number range from 0.18 to 0.49 and Reynolds number range from 6.1 to 13.4 million. The maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests (0.66 deg per chord length of travel) in contradistinction to the results of the flight tests of two other airplanes. The tests indicated that the Mach and Reynolds numbers effects were of sufficient importance to produce more than a twofold variation in the increment of due to a given rate of change of angle of attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1951
- Accession Number
- ADA380413
Entities
People
- Burnett L. Gadeberg
Organizations
- National Aeronautics and Space Administration