Transonic Wind Tunnel Test of a 16-Percent-Thick Circulation Control Airfoil with One-Percent Asymmetric Camber.
Abstract
A two-dimensional circulation control (CC) airfoil model was tested in the 7- by 10-foot transonic wind tunnel at the David W. Taylor Naval Ship R&D Center. Test conditions covered a range of free-stream Mach numbers (0.3 to 0.8), angles of attack (-10 to +6 deg), and blown jet pressure ratios (0 to 3.0). These data provided the first information on the influence of angle of attack on CC airfoil drag and lift augmentation at transonic speeds. The tested CC airfoil NCCR 1610-8054S was quasi-elliptical in shape, having a 16-percent thickness to chord ratio, with 1-percent maximum camber occurring at 70-percent chord. The program objectives were to achieve improved performance at transonic speeds while maintaining the characteristically high-lift augmentation at low subsonic operation. These objectives required nonsymmetrical thickness and camber distributions for the airfoil. Performance goals were qualitatively substantiated by the transonic test data. At 2-deg angle of attack, a maximum lift coefficient of 2.1 was obtained at M free-stream Mach no. = 0.3; while for M free-stream Mach no. = 0.6 at the same angle, the maximum lift coefficient was 0.76. As a high-lift device the airfoil was very effective at and below M free-stream Mach no. = 0.4. As a means of direct lift control the airfoil remained effective up through M free-stream Mach no. = 0.7. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1982
- Accession Number
- ADA116298
Entities
People
- David W Taylor
- Joseph B. Wilkerson
- Peter S. Montana