Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sai Venkata Phanindra Chary Arendra
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Diagonal of a Rectangle when breadth and area are given
Diagonal=sqrt(((Area)^2/(Breadth)^2)+(Breadth)^2) GO
Diagonal of a Rectangle when length and area are given
Diagonal=sqrt(((Area)^2/(Length)^2)+(Length)^2) GO
Side of a Kite when other side and area are given
Side A=(Area*cosec(Angle Between Sides))/Side B GO
Perimeter of rectangle when area and rectangle length are given
Perimeter=(2*Area+2*(Length)^2)/Length GO
Buoyant Force
Buoyant Force=Pressure*Area GO
Perimeter of a square when area is given
Perimeter=4*sqrt(Area) GO
Diagonal of a Square when area is given
Diagonal=sqrt(2*Area) GO
Length of rectangle when area and breadth are given
Length=Area/Breadth GO
Breadth of rectangle when area and length are given
Breadth=Area/Length GO
Pressure when force and area are given
Pressure=Force/Area GO
Stress
Stress=Force/Area GO

4 Other formulas that calculate the same Output

Zero-lift drag coefficient for given required thrust
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift GO
Zero-lift drag coefficient at minimum required thrust
Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Parasite Drag Coefficient at zero lift
Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO
Zero-lift drag coefficient for minimum power required
Zero-lift drag coefficient=Coefficient of drag due to lift/3 GO

Zero-lift drag coefficient for given lift coefficient Formula

Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
C<sub>D,0</sub>=(T/(P<sub>dynamic*A))-((C<sub>L</sub>^2)/(pi*e*AR))
More formulas
Drag for a level, unaccelerated flight at negligible thrust angle GO
Coefficient of Drag for given thrust-to-weight ratio GO
Coefficient of Drag for given thrust and weight GO
Zero-lift drag coefficient for given required thrust GO
Lift-induced drag coefficient for given required thrust GO
Zero-lift drag coefficient at minimum required thrust GO

How is the reference area chosen?

The reference area is arbitrary in principle. It is chosen as the area that is characteristic of the object considered. As an example, in aircraft aerodynamics, typically the planform area of the wing is chosen as the reference area for both lift and drag coefficients of the wing.

How to Calculate Zero-lift drag coefficient for given lift coefficient?

Zero-lift drag coefficient for given lift coefficient calculator uses Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) to calculate the Zero-lift drag coefficient, The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft. Zero-lift drag coefficient and is denoted by CD,0 symbol.

How to calculate Zero-lift drag coefficient for given lift coefficient using this online calculator? To use this online calculator for Zero-lift drag coefficient for given lift coefficient, enter Thrust of an aircraft (T), Dynamic Pressure (Pdynamic), Area (A), lift coefficient (CL), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Zero-lift drag coefficient for given lift coefficient calculation can be explained with given input values -> -15.715494 = (100/(10*50))-((10^2)/(pi*0.5*4)).

FAQ

What is Zero-lift drag coefficient for given lift coefficient?
The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft and is represented as CD,0=(T/(Pdynamic*A))-((CL^2)/(pi*e*AR)) or Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)). The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The area is the amount of two-dimensional space taken up by an object, The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. , The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
How to calculate Zero-lift drag coefficient for given lift coefficient?
The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressre, reference area, oswald efficiency factor and aspect ratio of wing of the aircraft is calculated using Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)). To calculate Zero-lift drag coefficient for given lift coefficient, you need Thrust of an aircraft (T), Dynamic Pressure (Pdynamic), Area (A), lift coefficient (CL), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Thrust of an aircraft, Dynamic Pressure, Area, lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Zero-lift drag coefficient?
In this formula, Zero-lift drag coefficient uses Thrust of an aircraft, Dynamic Pressure, Area, lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift
  • Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift
  • Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)
  • Zero-lift drag coefficient=Coefficient of drag due to lift/3
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