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Calculate Induced Drag and Induced Drag Coefficient CDi of Airplane Method to Calculate the Induced Drag and the Induced Drag Coefficient of an Airplane flying at Standard Sealevel Conditions 

Aerospace



Induced Drag Coefficient and Induced Drag of an Airplane In order to calculate the Induced Drag Coefficient (CDi) and the Induced Drag (Di) of an Airplane which is flying at Standard sealevel conditions... 

The following values are required, Wing Area in feet^2/sec. How much Lift is being generated by the Wing in lb Flight Velocity or the velocity at which the airplane is flying in miles/h The Wing Span in ft the Span Efficiency Factor, e value
Performing the Calculation, we get Aspect Ratio = AR = b^2/S = (Wing Span)^2/ Wing Area.
The value of the Dynamic Pressure q = .5*density*velocity^2.
The Induced Drag Coefficient of Airplane Value = CDi = Cl^2/pi*e*AR
and the Induced Drag of Airplane = Di = q*S*CDi in lb 

Download Free Program to Calculate the Induced Drag and the Induced Drag Coefficient

