Thrust of aircraft required for level, unaccelerated flight 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 area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust of aircraft required for level, unaccelerated flight [T]

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Formula

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Thrust of aircraft required for level, unaccelerated flight

Formula

`"T" = "P"_{"dynamic"}*"A"*"C"_{"D"}`

Example

`"100N"="10Pa"*"20m²"*"0.5"`

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Thrust of aircraft required for level, unaccelerated flight Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust = Dynamic Pressure*Area*Drag Coefficient
T = P_dynamic*A*C_D
This formula uses 4 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.
Area - (Measured in Square Meter) - The area is the amount of two-dimensional space taken up by an object.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

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
Drag Coefficient: 0.5 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = P_dynamic*A*C_D --> 10*20*0.5

Evaluating ... ...

T = 100

STEP 3: Convert Result to Output's Unit

100 Newton --> No Conversion Required

FINAL ANSWER

100 Newton <-- Thrust

(Calculation completed in 00.020 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

Thrust of aircraft required for level, unaccelerated flight Formula

Thrust = Dynamic Pressure*Area*Drag Coefficient
T = P_dynamic*A*C_D

What is steady, level flight?

Steady, level flight is when an airplane flies at a constant velocity along a level trajectory (parallel to the earth).

How to Calculate Thrust of aircraft required for level, unaccelerated flight?

Thrust of aircraft required for level, unaccelerated flight calculator uses Thrust = Dynamic Pressure*Area*Drag Coefficient to calculate the Thrust, The Thrust of aircraft required for level, unaccelerated flight (and negligible thrust angle) 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 Thrust of aircraft required for level, unaccelerated flight using this online calculator? To use this online calculator for Thrust of aircraft required for level, unaccelerated flight, enter Dynamic Pressure (P_dynamic), Area (A) & Drag Coefficient (C_D) and hit the calculate button. Here is how the Thrust of aircraft required for level, unaccelerated flight calculation can be explained with given input values -> 40 = 10*20*0.5.

FAQ

What is Thrust of aircraft required for level, unaccelerated flight?

The Thrust of aircraft required for level, unaccelerated flight (and negligible thrust angle) 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 or Thrust = Dynamic Pressure*Area*Drag Coefficient. 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 & Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

How to calculate Thrust of aircraft required for level, unaccelerated flight?

The Thrust of aircraft required for level, unaccelerated flight (and negligible thrust angle) 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*Drag Coefficient. To calculate Thrust of aircraft required for level, unaccelerated flight, you need Dynamic Pressure (P_dynamic), Area (A) & Drag Coefficient (C_D). With our tool, you need to enter the respective value for Dynamic Pressure, Area & 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 Thrust?

In this formula, Thrust uses Dynamic Pressure, Area & Drag Coefficient. We can use 7 other way(s) to calculate the same, which is/are as follows -

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