Lift Coefficient given Minimum required Thrust Calculator

✖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.ⓘ 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 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 given Minimum required Thrust [C_L]

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Lift Coefficient given Minimum required Thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

Oswald Efficiency Factor: 0.51 --> No Conversion Required
Aspect Ratio of a Wing: 4 --> No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required
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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = sqrt(pi*e*AR*((T/(P_dynamic*A))-C_D,0)) --> sqrt(pi*0.51*4*((100/(10*20))-0.31))

Evaluating ... ...

C_L = 1.10348598202759

STEP 3: Convert Result to Output's Unit

1.10348598202759 --> No Conversion Required

FINAL ANSWER

1.10348598202759 ≈ 1.103486 <-- Lift Coefficient

(Calculation completed in 00.020 seconds)

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Created by Vinay Mishra

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

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< 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 Coefficient given Minimum required Thrust Formula

LaTeX Go

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

What is the condition for steady, level flight?

The loads acting on the aircraft should be in static equilibrium when the aircraft is in a steady, unaccelerated, level flight condition.

How to Calculate Lift Coefficient given Minimum required Thrust?

Lift Coefficient given Minimum required Thrust calculator uses Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)) to calculate the Lift Coefficient, The Lift Coefficient given Minimum required Thrust equation allows us to calculate the lift coefficient for a given minimum required thrust, assuming level flight conditions where lift equals weight and thrust equals drag. Lift Coefficient is denoted by C_L symbol.

How to calculate Lift Coefficient given Minimum required Thrust using this online calculator? To use this online calculator for Lift Coefficient given Minimum required Thrust, enter Oswald Efficiency Factor (e), Aspect Ratio of a Wing (AR), Thrust (T), Dynamic Pressure (P_dynamic), Area (A) & Zero Lift Drag Coefficient (C_D,0) and hit the calculate button. Here is how the Lift Coefficient given Minimum required Thrust calculation can be explained with given input values -> 1.414058 = sqrt(pi*0.51*4*((100/(10*20))-0.31)).

FAQ

What is Lift Coefficient given Minimum required Thrust?

The Lift Coefficient given Minimum required Thrust equation allows us to calculate the lift coefficient for a given minimum required thrust, assuming level flight conditions where lift equals weight and thrust equals drag and is represented as C_L = sqrt(pi*e*AR*((T/(P_dynamic*A))-C_D,0)) or Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)). 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, 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 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.

How to calculate Lift Coefficient given Minimum required Thrust?

The Lift Coefficient given Minimum required Thrust equation allows us to calculate the lift coefficient for a given minimum required thrust, assuming level flight conditions where lift equals weight and thrust equals drag is calculated using Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)). To calculate Lift Coefficient given Minimum required Thrust, you need Oswald Efficiency Factor (e), Aspect Ratio of a Wing (AR), Thrust (T), Dynamic Pressure (P_dynamic), Area (A) & Zero Lift Drag Coefficient (C_D,0). With our tool, you need to enter the respective value for Oswald Efficiency Factor, Aspect Ratio of a Wing, Thrust, Dynamic Pressure, 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 Lift Coefficient?

In this formula, Lift Coefficient uses Oswald Efficiency Factor, Aspect Ratio of a Wing, Thrust, Dynamic Pressure, Area & Zero Lift Drag Coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -

Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
Lift Coefficient = Weight of Body*Drag Coefficient/Thrust

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