For Mach number 0.6, obtain the lift response of the airfoil to the arbitrary motion given by Problem 3.10.

Problem 3.10

Obtain the time variation of the sectional lift coefficient for an airfoil which is pitching about its leading edge as shown in Fig. 3.15 using 

(i) unsteady aerodynamics, 

(ii) quasi unsteady aerodynamics, 

(iii) quasi steady aerodynamics. 

Plot the lift coefficient vs time curve for all three cases.

Fig. 3.15

Transcribed Image Text:

0 4 8 S