NACA 0012 aerofoillow-Reynolds-number flowsflow separationtransitionlaminar separation bubblenegative liftNumerical investigations on the flow over NACA 0012 aerofoil are carried out to provide better understanding of the unusual lift characteristics exhibited by this aerofoil at low Reynolds numbers. ...
Force and supporting particle image velocimetry measurements were performed on a plunging NACA 0012 airfoil at a Reynolds number of 10,000, at pre-stall, stall, and post-stall angles of attack. The lift coefficient for pre-stall and stall angles of attack at larger amplitudes showed abrupt bifu...
Note: In 3D, the lift coefficient is nondimensionalized by area instead of length: Graph comparing simulation results and experimental data of the lift coefficient on a NACA 0012 airfoil at various angles of attack. As illustrated in the above graph, no discernible discrepancy between the computat...
Coefficient of liftCFD simulations were conducted to estimate the effect of angle of attack on coefficient of lift of NACA 0012 airfoil blade structure. C grid unstructured mesh wRao, K.V. SreenivasD.G., KemparajSocial Science Electronic Publishing...
This numerical study models the NACA 0012 symmetric airfoil and analyzes the impact of various design modifications to enhance its lift-drag ratios. The numerical simulation initially is conducted on the 2-D airfoil and the results are compared to the standard data for validation. Based on the ...
We prove the applicability of this model to all planar motions of airfoil; plunging, pitching and flapping. An important aspect of currently-proposed model is capturing the time-averaged value of aerodynamic lift coefficient.doi:10.48550/arXiv.1502.06431Muhammad Saif Ullah Khalid...
Using the adjusted drag model, we start by calculating the lift coefficient of LDmax as follows: LDmax=14kCDmin+2kCLminD2−2kCLminD=21.2CL=CDmink+CLminD2=0.0200.05236+0.202=0.6496 The L/D as a function of requested airspeeds are plotted in Figures 20-11 and 20-12. Figure 20-11 ...
the physical aspects of the analytical expressions for the lift coefficient of the plate-plate airfoil are discussed, including Newton’s sine-squared law, Rayleigh’s lift formula, thin-airfoil theory and viscous-flow lift formula. The vortex-force theory is described to provide a solid foundation...
Separation Control on HIgh Angle of Attack Airfoil Using Plasma Actuators It was instrumented for surface pressure measurements that were used to calculate lift coefficients. Mean velocity profiles downstream of the airfoil were used to determine the drag coefficient. In addition to these, smoke streakl...
Experimental investigation of the active flow control on a two-dimensional wind turbine airfoil Under the same unsteady freestream conditions, the averaged lift coefficient at 19 degree angle of incidence was enhanced by up to 20% while the pressure... G Wang - Dissertations & Theses - Gradworks...