Minimum Thrust of aircraft required Calculator

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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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform 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 is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.ⓘ Coefficient Of Drag Due to Lift [C_D,i]			+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 of aircraft required [T]

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Formula

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Minimum Thrust of aircraft required

Formula

`"T" = "P"_{"dynamic"}*"S"*("C"_{"D,0"}+"C"_{"D,i"})`

Example

`"99.2N"="10Pa"*"8m²"*("0.31"+"0.93")`

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Minimum Thrust of aircraft required Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

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.
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 planform 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.
Coefficient Of Drag Due to Lift - The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.

STEP 1: Convert Input(s) to Base Unit

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
Coefficient Of Drag Due to Lift: 0.93 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = P_dynamic*S*(C_D,0+C_D,i) --> 10*8*(0.31+0.93)

Evaluating ... ...

T = 99.2

STEP 3: Convert Result to Output's Unit

99.2 Newton --> No Conversion Required

FINAL ANSWER

99.2 Newton <-- Thrust

(Calculation completed in 00.004 seconds)

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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 Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

Sai Venkata Phanindra Chary Arendra 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 of aircraft required Formula

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

In a passenger airplane, how much thrust is required?

In a passenger airplane, at least enough thrust is required to keep the airplane flying at the speed of minimum drag.

How to Calculate Minimum Thrust of aircraft required?

Minimum Thrust of aircraft required calculator uses Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift) to calculate the Thrust, The Minimum Thrust of aircraft required for 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 of aircraft required using this online calculator? To use this online calculator for Minimum Thrust of aircraft required, enter Dynamic Pressure (P_dynamic), Reference Area (S), Zero Lift Drag Coefficient (C_D,0) & Coefficient Of Drag Due to Lift (C_D,i) and hit the calculate button. Here is how the Minimum Thrust of aircraft required calculation can be explained with given input values -> 69.92 = 10*8*(0.31+0.93).

FAQ

What is Minimum Thrust of aircraft required?

The Minimum Thrust of aircraft required for 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*S*(C_D,0+C_D,i) or Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift). 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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform 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 & The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.

How to calculate Minimum Thrust of aircraft required?

The Minimum Thrust of aircraft required for 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*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift). To calculate Minimum Thrust of aircraft required, you need Dynamic Pressure (P_dynamic), Reference Area (S), Zero Lift Drag Coefficient (C_D,0) & Coefficient Of Drag Due to Lift (C_D,i). With our tool, you need to enter the respective value for Dynamic Pressure, Reference Area, Zero Lift Drag Coefficient & Coefficient Of Drag Due to Lift 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, Reference Area, Zero Lift Drag Coefficient & Coefficient Of Drag Due to Lift. 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*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))
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

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