Some Wind Tunnel Results
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
jk
and
C
μ
, respectively
CFJ injection and suction mass flow rates
Comparison of power required
to achieve
C
L
=4.22 for two CFJ airfoils
Super-Circulation Airfoil
at AoA equal to 39°
