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The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft. Check FAQs
CD,i=(TPdynamic⋅S)-CD,0
CD,i - Coefficient Of Drag Due to Lift?T - Thrust?Pdynamic - Dynamic Pressure?S - Reference Area?CD,0 - Zero Lift Drag Coefficient?

Lift-Induced Drag Coefficient given required Thrust Example

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Here is how the Lift-Induced Drag Coefficient given required Thrust equation looks like with Values.

Here is how the Lift-Induced Drag Coefficient given required Thrust equation looks like with Units.

Here is how the Lift-Induced Drag Coefficient given required Thrust equation looks like.

0.94Edit=(100Edit10Edit⋅8Edit)-0.31Edit
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Lift-Induced Drag Coefficient given required Thrust Solution

Follow our step by step solution on how to calculate Lift-Induced Drag Coefficient given required Thrust?

FIRST Step Consider the formula
CD,i=(TPdynamic⋅S)-CD,0
Next Step Substitute values of Variables
∴ CD,i=(100N10Pa⋅8m²)-0.31
Next Step Prepare to Evaluate
∴ CD,i=(10010⋅8)-0.31
LAST Step Evaluate
∴CD,i=0.94

Lift-Induced Drag Coefficient given required Thrust Formula Elements

Variables
Coefficient Of Drag Due to Lift
The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft.
Symbol: CD,i
Measurement: NAUnit: Unitless
Note: Value should be greater than 0.
Formulas to find Coefficient Of Drag Due to LiftOpen Variable
Thrust
The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
Symbol: T
Measurement: ForceUnit: N
Note: Value should be greater than 0.
Formulas to find ThrustOpen Variable
Dynamic Pressure
Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.
Symbol: Pdynamic
Measurement: PressureUnit: Pa
Note: Value should be greater than 0.
Formulas to find Dynamic PressureOpen Variable
Reference Area
The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's platform area is called the reference wing area or simply wing area.
Symbol: S
Measurement: AreaUnit: m²
Note: Value should be greater than 0.
Formulas to find Reference AreaOpen Variable
Zero Lift Drag Coefficient
Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
Symbol: CD,0
Measurement: NAUnit: Unitless
Note: Value should be greater than 0.
Formulas to find Zero Lift Drag CoefficientOpen Variable

Other Formulas to find Coefficient Of Drag Due to Lift

​Go Coefficient of Drag due to Lift for Minimum Power required
CD,i=3⋅CD,0

Other formulas in Lift and Drag Requirements category

​Go Drag for Level and Unaccelerated Flight
FD=T⋅cos(σT)
​Go Lift for Unaccelerated Flight
FL=Wbody-T⋅sin(σT)
​Go Drag for Level and Unaccelerated Flight at Negligible Thrust Angle
FD=Pdynamic⋅A⋅CD
​Go Lift for Level and Unaccelerated Flight at Negligible Thrust Angle
FL=Pdynamic⋅A⋅CL

How to Evaluate Lift-Induced Drag Coefficient given required Thrust?

Lift-Induced Drag Coefficient given required Thrust evaluator uses Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient to evaluate the Coefficient Of Drag Due to Lift, The Lift-Induced Drag Coefficient given required Thrust is a dimensionless quantity used in aerodynamics to quantify the amount of drag produced by the generation of lift, it represents the ratio of the lift-induced drag force to the dynamic pressure and the wing area. Coefficient Of Drag Due to Lift is denoted by CD,i symbol.

How to evaluate Lift-Induced Drag Coefficient given required Thrust using this online evaluator? To use this online evaluator for Lift-Induced Drag Coefficient given required Thrust, enter Thrust (T), Dynamic Pressure (Pdynamic), Reference Area (S) & Zero Lift Drag Coefficient (CD,0) and hit the calculate button.

FAQs on Lift-Induced Drag Coefficient given required Thrust

What is the formula to find Lift-Induced Drag Coefficient given required Thrust?
The formula of Lift-Induced Drag Coefficient given required Thrust is expressed as Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient. Here is an example- 0.94 = (100/(10*8))-0.31.
How to calculate Lift-Induced Drag Coefficient given required Thrust?
With Thrust (T), Dynamic Pressure (Pdynamic), Reference Area (S) & Zero Lift Drag Coefficient (CD,0) we can find Lift-Induced Drag Coefficient given required Thrust using the formula - Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient.
What are the other ways to Calculate Coefficient Of Drag Due to Lift?
Here are the different ways to Calculate Coefficient Of Drag Due to Lift-
  • Coefficient Of Drag Due to Lift=3*Zero Lift Drag CoefficientOpenImg
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