- Tested CFJ Airfoil Geometry
- Wind Tunnel Setup
- Wind Tunnel Test Results for lift coefficient and drag polar
- Baseline Airfoil AoA=20° Flow Separated
- PIV for baseline airfoil at AoA equal to 20°
- CFJ Airfoil AoA=43°, Flow Attached ;
- Flow visualization for separated flow, AoA equal to 46°
- PIV measured normalized velocity contours and streamlines of attached flow, AoA equal to 43°
- PIV measured normalized velocity contours and streamlines of separated flow, AoA equal to 46°
- Injection momentum coefficient, streamlines, and Mach contours at AoA equal to 39°
- Lift and momentum coefficients
- Drag polar
- Ratio of CFJ to baseline lift coefficient and stall margin vs
*C*_{jk} - Minimum drag reduction vs
*C*and_{jk}*C*, respectively_{μ} - CFJ injection and suction mass flow rates
- Comparison of power required to achieve
*C*=4.22 for two CFJ airfoils_{L} - Super-Circulation Airfoil at AoA equal to 39°