Figure 1
Schematic of wind tunnel.
Figure 2
Model in test chamber.
Figure 3
Rake of hot wire sensors.
Figure 4
Airfoil, rake and sensors fixed in the test chamber.
Figure 5
Block diagram of data acquisition system.
Figure 6
PSD values of a hot wire.
Figure 7
Hydraulic oscillating alpha-mechanism system.
Figure 8
Computational domain.
Figure 9
(a) Computational grid; (b) close-up view.
Figure 10
Y+ calculated on the airfoil wall.
Figure 11
Lift coefficient distribution, Mach = 0.4.
Figure 12
Lift coefficient distribution, Mach = 0.6.
Figure 13
Linear correlation coefficient diagram for hot wire sensors.
Figure 14
Time history of hot wires output signals at AOA = 4º.
Figure 15
Sensors energy level at angle of attack of 3°.
Figure 16
Sensors energy level at angle of attack of 6°.
Figure 17
Instantaneous voltages of three sensors, pitch oscillation α(t) = 3 + 3 sin (2πt/T - π/2), frequency = 3Hz, Mach = 0.4.
Figure 18
RMS variations in a complete cycle.
Figure 19
Coefficient of linear correlation between sensors S7 and S14.
Figure 20
Streamwise velocity profile at x/c = 0.25, Mach = 0.4.
Figure 21
Streamwise velocity profile at x/c = 0.25, Mach = 0.4.
Figure 22
Streamwise velocity profile at x/c = 0.25, Mach = 0.4.
Figure 23
Streamwise velocity profile at x/c = 0.25, Mach = 0.6.
Figure 24
Streamwise velocity profile at x/c = 0.25, Mach = 0.6.
Figure 25
Streamwise velocity profile at x/c = 0.25, Mach = 0.6.
Figure 26
Streamwise velocity profile at x/c = 0.5, Mach = 0.4.
Figure 27
Streamwise velocity profile, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.4.
Figure 28
Streamwise velocity profile, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.4.
Figure 29
Streamwise velocity profile, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.6.
Figure 30
Streamwise velocity profile, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.6.
Figure 31
Pressure Coefficient distribution over the airfoil obtained from numerical solution, Mach = 0.6.
Figure 32
Mach contour, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.4, Alpha = 5°.
Figure 33
Mach contour, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.4, Alpha = 6°
Figure 34
Mach contour, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.6, Alpha = 5°.
Figure 35
Mach contour, pitch motion α(t) = 3 + 3 sin(ωt), frequency = 3 Hz, Mach = 0.6, Al