Aerodynamic Coefficients of an Oscillating Airfoil with Control Surface in Two-Dimensional Subsonic Flow

1953 ◽  
Vol 20 (3) ◽  
pp. 153-159 ◽  
Author(s):  
A. I. VAN DE VOOREN
Keyword(s):  
Subsonic Flow ◽  
Control Surface ◽  
Two Dimensional ◽  
Aerodynamic Coefficients ◽  
Oscillating Airfoil

CFD Analysis of Oscillating Airfoil during Pitch Cycle

2012 ◽  
Vol 152-154 ◽  
pp. 906-911
Author(s):  
Ahmad Kamran ◽  
Zhi Gang Wu ◽  
Muhammad Amjad Sohail
Keyword(s):  
Experimental Data ◽  
Subsonic Flow ◽  
Navier Stokes ◽  
Cfd Analysis ◽  
Two Dimensional ◽  
Turbulent Model ◽  
Pitching Airfoil ◽  
First Order ◽  
Implicit Solver ◽  
Oscillating Airfoil

This research paper presents the CFD analysis of oscillating airfoil during pitch cycle. Unsteady subsonic flow is simulated for pitching airfoil at Mach number 0.283 and Reynolds number 3.45 millions. Turbulent effects are also considered for this study by using K-ω SST turbulent model. Two-dimensional unsteady compressible Navier-Stokes code including two-equation turbulence model and PISO pressure velocity coupling is used. Pressure based implicit solver with first order implicit unsteady formulation is used. The simulated pitch cycle results are compared with the available experimental data.

A Two-Dimensional Aerofoil with a Control Surface Oscillating at Low Frequency in High Subsonic Flow

1974 ◽  
Vol 25 (3) ◽  
pp. 186-198 ◽  
Author(s):  
D Nixon
Keyword(s):  
Subsonic Flow ◽  
Deflection Angle ◽  
Low Frequency ◽  
Frequency Parameter ◽  
Control Surface ◽  
Two Dimensional ◽  
Subcritical Flow ◽  
Surface Stiffness ◽  
Aerodynamic Derivatives ◽  
Surface Deflection

SummaryThe aerodynamic derivatives for a two-dimensional aerofoil with an oscillating control surface in a high subcritical flow are calculated using the method of Nixon. The aerofoil is assumed to be symmetric and at zero incidence with a zero mean control surface deflection angle. With the exception of the control surface stiffness derivative the magnitudes of the aerodynamic derivatives are greater than the corresponding linear values by between 15–35 per cent; the greatest difference occurs for low values of the frequency parameter. The magnitude of the control surface stiffness derivative is less than the corresponding linear value by the order 10–15 per cent.

The High Subsonic Flow Around a Two-Dimensional Aerofoil with a Trailing Edge Control Surface

1973 ◽  
Vol 24 (4) ◽  
pp. 273-283 ◽  
Author(s):  
D Nixon
Keyword(s):  
Linear Theory ◽  
Subsonic Flow ◽  
Lift Coefficient ◽  
Integral Equation Method ◽  
Control Surface ◽  
Two Dimensional ◽  
Front Part ◽  
Trailing Edge ◽  
Moment Coefficient ◽  
Standard Linear

SummaryThe effect of the operation of a 15 per cent trailing edge control surface on the flow around a two-dimensional aerofoil in a high subsonic shock-free condition is investigated using the integral equation method developed by Nixon and Hancock. The effect of retaining the non-linearities in the transonic potential equation is to increase considerably the magnitude of the pressures over the front part of the aerofoil in comparison with the pressure found using a modified linearised theory in which significant second-order terms in the boundary conditions are retained. The magnitude of the lift coefficient and the pitching moment coefficient are increased by 10-15 per cent over the values found using the modified linear theory, and by 20 per cent over the values found using standard linear theory. However, the magnitude of the hinge-moment coefficient is decreased by the order of 20 per cent compared with the modified linear values and by 30 per cent when compared to the standard linear values.

scholarly journals Aerodynamic Optimization of Wing by Camber Morphing using Cfd

2020 ◽  
Vol 9 (5) ◽  
pp. 122-130
Keyword(s):  
Subsonic Flow ◽  
Lift Coefficient ◽  
Cfd Analysis ◽  
Two Dimensional ◽  
Aerodynamic Coefficients ◽  
Aerodynamic Optimization ◽  
Aerodynamic Efficiency ◽  
Naca0012 Airfoil ◽  
Morphing Technology ◽  
Lift And Drag

This paper presents the CFD analysis of the 2-Dimensional NACA0012 airfoil carried out for identifying its aerodynamic coefficients (Lift and Drag coefficients), then further implementing morphing technology on the same two-dimensional NACA0012 airfoil, again carrying out CFD analysis to determine its aerodynamic coefficients (Lift coefficient (CL) and Drag coefficient (CD), then comparing the results of both the airfoil shapes particularly to the amount of Lift generated to prove that morphing airfoil produces more amount of Lift when compared to typical airfoil shapes. Using ANSYS Design modeler airfoil geometry was created and morphing shape could be achieved by XFLR5 software further the analysis is carried out using FLUENT 18.1 at subsonic flow. This morphing enables to improve aerodynamic efficiency.

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