Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ 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

2 Other formulas that calculate the same Output

Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Coefficient of Drag due to lift for minimum power required
Coefficient of drag due to lift=3*Zero-lift drag coefficient GO

Lift-induced drag coefficient for given required thrust Formula

Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient
C<sub>D,i</sub>=(T/(P<sub>dynamic*A))-C<sub>D,0</sub>
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
Zero-lift drag coefficient for given lift coefficient GO
Zero-lift drag coefficient at minimum required thrust GO

How to obtain total drag for an aircraft?

Induced drag (also called drag due to lift) must be added to the parasitic drag to find the total drag on an aircraft

How to Calculate Lift-induced drag coefficient for given required thrust?

Lift-induced drag coefficient for given required thrust calculator uses Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient to calculate the Coefficient of drag due to lift, The Lift-induced drag coefficient for given required thrust in a steady, level flight depends upon the zero-lift drag coefficient of an aircraft. . Coefficient of drag due to lift and is denoted by CD,i symbol.

How to calculate Lift-induced drag coefficient for given required thrust using this online calculator? To use this online calculator for Lift-induced drag coefficient for given required thrust, enter Thrust of an aircraft (T), Dynamic Pressure (Pdynamic), Area (A) and Zero-lift drag coefficient (CD,0) and hit the calculate button. Here is how the Lift-induced drag coefficient for given required thrust calculation can be explained with given input values -> 0.1839 = (100/(10*50))-0.0161.

FAQ

What is Lift-induced drag coefficient for given required thrust?
The Lift-induced drag coefficient for given required thrust in a steady, level flight depends upon the zero-lift drag coefficient of an aircraft. and is represented as CD,i=(T/(Pdynamic*A))-CD,0 or Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient. 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 and The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude.
How to calculate Lift-induced drag coefficient for given required thrust?
The Lift-induced drag coefficient for given required thrust in a steady, level flight depends upon the zero-lift drag coefficient of an aircraft. is calculated using Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient. To calculate Lift-induced drag coefficient for given required thrust, you need Thrust of an aircraft (T), Dynamic Pressure (Pdynamic), Area (A) and Zero-lift drag coefficient (CD,0). With our tool, you need to enter the respective value for Thrust of an aircraft, Dynamic Pressure, Area and Zero-lift drag coefficient 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 Coefficient of drag due to lift?
In this formula, Coefficient of drag due to lift uses Thrust of an aircraft, Dynamic Pressure, Area and Zero-lift drag coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)
  • Coefficient of drag due to lift=3*Zero-lift drag coefficient
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