Minimum Thrust required for given lift coefficient Calculator

↳

⤿

Aircraft Performance

Aircraft Design

Introduction and Governing Equations

Static Stability and Control

⤿

⤿

Thrust and Power Requirements

Lift and Drag Requirements

✖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%
✖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]

⎘ Copy

👎

Formula

✖

Minimum Thrust required for given lift coefficient

Formula

`"T" = "P"_{"dynamic"}*"A"*("C"_{"D,0"}+(("C"_{"L"}^2)/(pi*"e"*"AR")))`

Example

`"99.76029N"="10Pa"*"20m²"*("0.31"+((("1.1")^2)/(pi*"0.51"*"4")))`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF

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 simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
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)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Level Flight » Thrust and Power Requirements » Minimum Thrust required for given lift coefficient

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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< 19 Thrust and Power Requirements Calculators

Minimum Thrust required for given weight

Go Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Minimum Thrust required for given lift coefficient

Go Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))

Minimum Thrust of aircraft required

Go Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)

Weight of aircraft for given required power

Go Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

Power required for given aerodynamic coefficients

Go Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient

Thrust Angle for Unaccelerated Level Flight for given Lift

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

Weight of aircraft in level, unaccelerated flight

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

Weight of aircraft for given coefficients of lift and drag

Go Weight of Body = Lift Coefficient*Thrust/Drag Coefficient

Thrust for given coefficients of lift and drag

Go Thrust = Drag Coefficient*Weight of Body/Lift Coefficient

Weight of aircraft for level, unaccelerated flight at negligible thrust angle

Go Weight of Body = Dynamic Pressure*Area*Lift Coefficient

Thrust of aircraft required for level, unaccelerated flight

Go Thrust = Dynamic Pressure*Area*Drag Coefficient

Thrust for Level and Unaccelerated Flight

Go Thrust = Drag Force/(cos(Thrust angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

Go Thrust angle = acos(Drag Force/Thrust)

Thrust-to-weight ratio

Go Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient

Thrust of aircraft required for given Lift-to-drag ratio

Go Thrust = Weight of Body/Lift-to-drag Ratio

Weight of aircraft for given Lift-to-drag ratio

Go Weight of Body = Thrust*Lift-to-drag Ratio

Power required for given total drag force

Go Power = Drag Force*Freestream Velocity

Power required for given required thrust of aircraft

Go Power = Freestream Velocity*Thrust

Thrust of aircraft required for given required power

Go Thrust = Power/Freestream Velocity

Minimum Thrust required for given lift coefficient Formula

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 in a steady, level flight is the force that moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket. 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 in a steady, level flight is the force that moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket 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 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, 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 in a steady, level flight is the force that moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket 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 7 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
Thrust = Weight of Body/Lift-to-drag Ratio
Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)
Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
Thrust = Power/Freestream Velocity

Home

FREE PDFs

🔍 Search