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The mean reattachment length exhibits a monotonic increase as the leading edge angle increases, while the maximum magnitudes of r.m.s and peak suction pressure coefficients are found to increase with increasing leading edge angle.
The underlying mechanisms and the cause for high thrust and power consumption are discussed in detail with more focus on relating such parameters directly with the geometrical features such as the amount of forking and fin leading edge angle.
At mid-upstroke there is a more pronounced decrease in the leading edge angle at low flight speeds than at higher flight speeds.
We estimated the leading edge angle, LE, as the angle of the leading edge flap (wrist P II t P III)i [pts 4 5 6]) relative to the triangle wrist P III)i P(IV i [pts 4 6 12] (Figs 1, 3).
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A downward deflected leading-edge flap is indicated by positive leading edge angles.
The optimization was carried out using eight design parameters for the turbine stage geometry optimization including stator and rotor number of blades, rotor leading edge beta angle, trailing edge beta angle, stagger angle, throat width, trailing half wedge angle and shroud tip clearance.
Aerodynamic parameters were found to show a strong dependence on the cosine of the leading edge sweep angle as well as the square root of the flap height.
The results show a linear decrease in the shedding frequency of nearly 40% as the leading edge separation angle is increased from 0° 90°.
From the phase averaged data, the velocity outside of the recirculation region is observed to decrease markedly as the leading edge separation angle is increased, which is suggested to be responsible for the observed changes in the shedding frequency.
Six different leading edge separation angles were created by altering the leading edge geometry.
The effects of impact angle, leading edge radius, and blade wedge angle are investigated.
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