Minimum Thrust of aircraft required 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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's platform 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 represents the contribution of lift-induced drag to the total drag experienced by an aircraft.ⓘ 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]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Thrust and Power Requirements Formulas PDF PDF Image

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 a measure of the kinetic energy per unit volume of a fluid in motion.
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 platform 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 represents the contribution of lift-induced drag to the total drag experienced by an aircraft.

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 00.008 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Level Flight » Aerospace » Thrust and Power Requirements » Minimum Thrust of aircraft required

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!

< 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)

Minimum Thrust of aircraft required Formula

LaTeX Go

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 refers to the least amount of propulsive force necessary to sustain flight under specific conditions, it's a critical parameter in aircraft design and operation, influencing factors such as fuel efficiency, range, and performance, in level flight, where the lift generated by the wings equals the aircraft's weight, the minimum thrust occurs when the total drag is minimized. 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 refers to the least amount of propulsive force necessary to sustain flight under specific conditions, it's a critical parameter in aircraft design and operation, influencing factors such as fuel efficiency, range, and performance, in level flight, where the lift generated by the wings equals the aircraft's weight, the minimum thrust occurs when the total drag is minimized 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 a measure of the kinetic energy per unit volume of a fluid in motion, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's platform 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 represents the contribution of lift-induced drag to the total drag experienced by an aircraft.

How to calculate Minimum Thrust of aircraft required?

The Minimum Thrust of Aircraft required refers to the least amount of propulsive force necessary to sustain flight under specific conditions, it's a critical parameter in aircraft design and operation, influencing factors such as fuel efficiency, range, and performance, in level flight, where the lift generated by the wings equals the aircraft's weight, the minimum thrust occurs when the total drag is minimized 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 3 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

Home

FREE PDFs

🔍 Search