The critical Mach number of several circulation control elliptic airfoils is calculated for various circulation and angle-of-attack conditions. The full inviscid compressible flow equations were solved by finite-difference relaxation methods. The sections examined are candidates for use on helicopter rotor blades. Comparison with conventional sections are made. It is shown that the elliptic circulation control airfoils have a significantly higher critical Mach number. (Author)
Critical Mach Numbers of Circulation Control Airfoils as Determined by Finite-Difference Methods
1972
36 pages
Report
Keine Angabe
Englisch
Aircraft , Fluid Mechanics , Rotor blades(Rotary wings) , Boundary layer control , Aerodynamic characteristics , Mach number , Compressible flow , Helicopter rotors , Airfoils , Trailing edge , Angle of attack , Drag , Numerical analysis , Difference equations , Partial differential equations , Relaxation time , Boundary layer transition , Flow fields , Subsonic flow , Transonic flow , Computer programs , Flow charting , Series(Mathematics) , Convergence , Potential theory , Finite difference methods , Stream functions
Mach Effects on Circulation Control and Jet Flap Airfoils
British Library Conference Proceedings | 2008
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