Lift-induced drag coefficient for given required thrust Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Drag during Level Unaccelerated Flight ↺

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust of an aircraft [T]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluidⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖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ⓘ Zero-lift drag coefficient [C_D,0]			+10% -10%

✖The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attackⓘ Lift-induced drag coefficient for given required thrust [C_D,i]

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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!

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< 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
CD,i=(T/(Pdynamic*A))-CD,0

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 C_D,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 (P_dynamic), Area (A) and Zero-lift drag coefficient (C_D,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 C_D,i=(T/(P_{dynamic*A))-C_D,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 (P_dynamic), Area (A) and Zero-lift drag coefficient (C_D,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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