The largest pitching moment coefficient for Re = 360000 is 0.6515, which indicates the most damaging condition for the blade at 130 degrees angle of attack. The largest lift and drag coefficient for Re = 50000 is 15.5069 at 5 degrees angle of attack.Yin Lu...
To investigate the effects of passive flow control using vortex generators (VGs) on the aerodynamic performance of a NACA0012 air foil. They performed experimental tests in a wind tunnel and found that the VGs significantly increased the lift coefficient and reduced the drag coefficient. To ...
advance the flow reattachment and lift coefficient recovery, reduce the hysteresis loop area of lift and pitchmoment coefficient circles and improve the aerodynamic characteristics of airfoil. The influence of different motion parame-ters and actuator setting parameters on the control effect was studied....
Experimental measurements of surface pressure distributions and wake profiles were obtained for a NACA0012 airfoil to determine the lift, drag, and pitching-moment coefficients for various configurations. The addition of a Gurney flap increased the maximum lift coefficient from 1.37 to 1.74, however the...
This section presents the outcomes and discussion of the NACA0012 transonic airfoil, summarised in Table 1, considering the aerodynamic shape optimization process. The primary constraint associated with this process is the lift coefficient (Cl=0.5), including the geometrical features of the symmetric ai...
o_ =_: _ b_ : i!;.f/:_''_ •_ }' __ i :' ° o :_ o __. }_. _ ,_,, ,' i o:' O j, 3.-digit reflex.- For some applications, for example, rotorcraft main rotors, it may be desirable to produce an airfoil with a quarter-chord pitching-moment coefficient of zer...
similar to those witnessed at the higher airspeeds in the 0.15 N·m setup.;For the routinely observed oscillations, namely those whose amplitudes did not exceed 6°, an analysis of the unsteady, viscous aerodynamic moment coefficient about the elastic axis revealed the effective aerody...
Lift coefficient, drag coefficient, pitching moment coefficient and lift to drag ratio of each airfoil was determined on several angles of attack from 0 to 10° (0°, 2°, 4°, 6°, 8°, 10°) and different ground clearances (h/c=0.2, 0.4, 0.6, 0.8, 1.0). The results of the ...
close to the value of the lift coefficient measured for this α (see Fig. 3(a)). Therefore, the present analysis supports, quantitatively, the initial explanation by Tank et al. (2017) who correlated negative lift to the fact that separation on the lower surface is delayed with respect to...
Surface flow studies specific to the NACA 0012 have confirmed the existence of a laminar separation bubble at transitional Reynolds numbers. Changes in the airfoil's aerodynamic performance, including the shape and slope of the lift curve, maximum lift coefficient, and static stall angle are ...