WorldofAerospace.googlepages.com                                                            Contact Us | Sitemap | Home 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 Sea-level 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 sea-level 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