Minimum Thrust required for given Lift Coefficient Calculator

✖Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The Area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+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 Lift Coefficient 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.ⓘ Lift Coefficient [C_L]			+10% -10%
✖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.ⓘ Oswald Efficiency Factor [e]			+10% -10%
✖The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a Wing [AR]			+10% -10%

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Minimum Thrust required for given Lift Coefficient [T]

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Minimum Thrust required for given Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)))
T = P_dynamic*A*(C_D,0+((C_L^2)/(pi*e*AR)))
This formula uses 1 Constants, 7 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
Area - (Measured in Square Meter) - The Area is the amount of two-dimensional space taken up by an object.
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.
Lift Coefficient - The Lift Coefficient 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.
Oswald Efficiency Factor - 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.
Aspect Ratio of a Wing - The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.

STEP 1: Convert Input(s) to Base Unit

Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area: 20 Square Meter --> 20 Square Meter No Conversion Required
Zero Lift Drag Coefficient: 0.31 --> No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Oswald Efficiency Factor: 0.51 --> No Conversion Required
Aspect Ratio of a Wing: 4 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = P_dynamic*A*(C_D,0+((C_L^2)/(pi*e*AR))) --> 10*20*(0.31+((1.1^2)/(pi*0.51*4)))

Evaluating ... ...

T = 99.7602904198419

STEP 3: Convert Result to Output's Unit

99.7602904198419 Newton --> No Conversion Required

FINAL ANSWER

99.7602904198419 ≈ 99.76029 Newton <-- Thrust

(Calculation completed in 00.004 seconds)

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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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< Thrust and Power Requirements Calculators

Thrust Angle for Unaccelerated Level Flight for given Lift

LaTeX Go Thrust Angle = asin((Weight of Body-Lift Force)/Thrust)

Weight of Aircraft in Level, Unaccelerated Flight

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

Thrust for Level and Unaccelerated Flight

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

Thrust Angle for Unaccelerated Level Flight for given Drag

LaTeX Go Thrust Angle = acos(Drag Force/Thrust)

Minimum Thrust required for given Lift Coefficient Formula

LaTeX Go

Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)))
T = P_dynamic*A*(C_D,0+((C_L^2)/(pi*e*AR)))

What are the factors for take-off thrust?

The factors for take-off thrust are runway length, runway elevation, runway slope, air temperature, wind speed, and minimum flight speed.

How to Calculate Minimum Thrust required for given Lift Coefficient?

Minimum Thrust required for given Lift Coefficient calculator uses Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))) to calculate the Thrust, The Minimum Thrust required for given Lift Coefficient represents the least amount of propulsive force necessary to maintain level flight while generating a specified lift coefficient, in level flight, where lift equals weight and thrust equals drag, achieving the minimum thrust required involves minimizing the drag coefficient. Thrust is denoted by T symbol.

How to calculate Minimum Thrust required for given Lift Coefficient using this online calculator? To use this online calculator for Minimum Thrust required for given Lift Coefficient, enter Dynamic Pressure (P_dynamic), Area (A), Zero Lift Drag Coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR) and hit the calculate button. Here is how the Minimum Thrust required for given Lift Coefficient calculation can be explained with given input values -> 75.36029 = 10*20*(0.31+((1.1^2)/(pi*0.51*4))).

FAQ

What is Minimum Thrust required for given Lift Coefficient?

The Minimum Thrust required for given Lift Coefficient represents the least amount of propulsive force necessary to maintain level flight while generating a specified lift coefficient, in level flight, where lift equals weight and thrust equals drag, achieving the minimum thrust required involves minimizing the drag coefficient and is represented as T = P_dynamic*A*(C_D,0+((C_L^2)/(pi*e*AR))) or Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))). Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion, The Area is the amount of two-dimensional space taken up by an object, Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift, The Lift Coefficient 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 & The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.

How to calculate Minimum Thrust required for given Lift Coefficient?

The Minimum Thrust required for given Lift Coefficient represents the least amount of propulsive force necessary to maintain level flight while generating a specified lift coefficient, in level flight, where lift equals weight and thrust equals drag, achieving the minimum thrust required involves minimizing the drag coefficient is calculated using Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing))). To calculate Minimum Thrust required for given Lift Coefficient, you need Dynamic Pressure (P_dynamic), Area (A), Zero Lift Drag Coefficient (C_D,0), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a Wing (AR). With our tool, you need to enter the respective value for Dynamic Pressure, Area, Zero Lift Drag Coefficient, Lift Coefficient, Oswald Efficiency Factor & 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 Thrust?

In this formula, Thrust uses Dynamic Pressure, Area, Zero Lift Drag Coefficient, Lift Coefficient, Oswald Efficiency Factor & Aspect Ratio of a Wing. We can use 3 other way(s) to calculate the same, which is/are as follows -

Thrust = Drag Force/(cos(Thrust Angle))
Thrust = Dynamic Pressure*Area*Drag Coefficient
Thrust = Drag Coefficient*Weight of Body/Lift Coefficient

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