Lift-Induced Drag Coefficient given required Thrust Calculator

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust [T]			+10% -10%
✖Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖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.ⓘ Reference Area [S]			+10% -10%
✖Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.ⓘ Zero Lift Drag Coefficient [C_D,0]			+10% -10%

✖The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft.ⓘ Lift-Induced Drag Coefficient given required Thrust [C_D,i]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Lift and Drag Requirements Formulas PDF PDF Image

Lift-Induced Drag Coefficient given required Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
C_D,i = (T/(P_dynamic*S))-C_D,0
This formula uses 5 Variables

Variables Used

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.
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.
Reference Area - (Measured in Square Meter) - 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.
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.

STEP 1: Convert Input(s) to Base Unit

Thrust: 100 Newton --> 100 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Reference Area: 8 Square Meter --> 8 Square Meter No Conversion Required
Zero Lift Drag Coefficient: 0.31 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i = (T/(P_dynamic*S))-C_D,0 --> (100/(10*8))-0.31

Evaluating ... ...

C_D,i = 0.94

STEP 3: Convert Result to Output's Unit

0.94 --> No Conversion Required

FINAL ANSWER

0.94 <-- Coefficient Of Drag Due to Lift

(Calculation completed in 00.008 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Level Flight » Aerospace » Lift and Drag Requirements » Lift-Induced Drag Coefficient given required Thrust

Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has verified this Calculator and 200+ more calculators!

< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

LaTeX Go Lift Force = Weight of Body-Thrust*sin(Thrust Angle)

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

LaTeX Go Drag Force = Thrust*cos(Thrust Angle)

Lift-Induced Drag Coefficient given required Thrust Formula

LaTeX Go

Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
C_D,i = (T/(P_dynamic*S))-C_D,0

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 given required Thrust?

Lift-Induced Drag Coefficient given required Thrust calculator uses Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient to calculate 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 C_D,i symbol.

How to calculate Lift-Induced Drag Coefficient given required Thrust using this online calculator? To use this online calculator for Lift-Induced Drag Coefficient given required Thrust, enter Thrust (T), Dynamic Pressure (P_dynamic), Reference Area (S) & Zero Lift Drag Coefficient (C_D,0) and hit the calculate button. Here is how the Lift-Induced Drag Coefficient given required Thrust calculation can be explained with given input values -> 0.94 = (100/(10*8))-0.31.

FAQ

What is Lift-Induced Drag Coefficient given required Thrust?

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 and is represented as C_D,i = (T/(P_dynamic*S))-C_D,0 or Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference 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 a measure of the kinetic energy per unit volume of a fluid in motion, 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 & Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.

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

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 is calculated using Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient. To calculate Lift-Induced Drag Coefficient given required Thrust, you need Thrust (T), Dynamic Pressure (P_dynamic), Reference Area (S) & Zero Lift Drag Coefficient (C_D,0). With our tool, you need to enter the respective value for Thrust, Dynamic Pressure, Reference Area & 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, Dynamic Pressure, Reference Area & Zero Lift Drag Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient

Home

FREE PDFs

🔍 Search