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

 

 Aerospace

 Aerospace Engineering

 Aeronautical Engineering

 Aeronautics

 Astronautics

 Space Exploration

 Aerospace Industry

 Aerospace Related Questions

 Aerospace Related Articles

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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