Lift Augmentation on Planar Airfoils in the Transonic Regime - a High Reynolds Number Wind Tunnel Study.
Abstract
Tests were carried out at Mach numbers of 0.75, 0.80, and 0.85 and a Reynolds number of 30,000,000/15 inch chord to determine the relative effectiveness of aft camber, jet flaps, or tangential slot blowing, either separately or in combination, to increase the maximum buffet-free lift coefficient. Aside from the force and moment measurements, airfoil surface pressure distributions were obtained. A finite difference calculation is carried out in one case to determine the angle of attack correction due to wall interference effect for the 20% porosity perforated wall wind tunnel. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1973
- Accession Number
- AD0912911
Entities
People
- Hideo Yoshihara
- Richard Magnus
- Robert Murray
- Wilbert Carter
Organizations
- General Dynamics