Thrust of Aircraft required for Level, Unaccelerated Flight 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%
✖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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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 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.
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 00.004 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 Sai Venkata Phanindra Chary Arendra

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

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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)

Thrust of Aircraft required for Level, Unaccelerated Flight Formula

LaTeX Go

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 also known as the "steady-state thrust," is the amount of thrust needed to balance the forces acting on the aircraft at a particular flight condition to maintain a constant velocity without any change in altitude or speed, in this state, the thrust produced by the aircraft's engines or propulsion system exactly matches the aerodynamic drag and other forces opposing the aircraft's motion through the air. 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 also known as the "steady-state thrust," is the amount of thrust needed to balance the forces acting on the aircraft at a particular flight condition to maintain a constant velocity without any change in altitude or speed, in this state, the thrust produced by the aircraft's engines or propulsion system exactly matches the aerodynamic drag and other forces opposing the aircraft's motion through the air and is represented as T = P_dynamic*A*C_D or Thrust = Dynamic Pressure*Area*Drag Coefficient. 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 & 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 also known as the "steady-state thrust," is the amount of thrust needed to balance the forces acting on the aircraft at a particular flight condition to maintain a constant velocity without any change in altitude or speed, in this state, the thrust produced by the aircraft's engines or propulsion system exactly matches the aerodynamic drag and other forces opposing the aircraft's motion through the air 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 3 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

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