Thrust for Level and Unaccelerated Flight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Thrust = Drag Force/(cos(Thrust angle))
T = FD/(cos(σT))
This formula uses 1 Functions, 3 Variables
Functions Used
cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(Angle)
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.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Thrust angle - (Measured in Radian) - Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.
STEP 1: Convert Input(s) to Base Unit
Drag Force: 99.99 Newton --> 99.99 Newton No Conversion Required
Thrust angle: 0.01 Radian --> 0.01 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
T = FD/(cos(σT)) --> 99.99/(cos(0.01))
Evaluating ... ...
T = 99.994999708321
STEP 3: Convert Result to Output's Unit
99.994999708321 Newton --> No Conversion Required
FINAL ANSWER
99.994999708321 99.995 Newton <-- Thrust
(Calculation completed in 00.004 seconds)

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!
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 for Level and Unaccelerated Flight Formula

Thrust = Drag Force/(cos(Thrust angle))
T = FD/(cos(σT))

What is thrust in flight?

Thrust is a force that moves an aircraft in the direction of the motion. It is created with a propeller, jet engine, or rocket.

How to Calculate Thrust for Level and Unaccelerated Flight?

Thrust for Level and Unaccelerated Flight calculator uses Thrust = Drag Force/(cos(Thrust angle)) to calculate the Thrust, Thrust for Level and Unaccelerated Flight is the thrust acting on an aeroplane for zero acceleration and zero flight path angle. Thrust is denoted by T symbol.

How to calculate Thrust for Level and Unaccelerated Flight using this online calculator? To use this online calculator for Thrust for Level and Unaccelerated Flight, enter Drag Force (FD) & Thrust angle T) and hit the calculate button. Here is how the Thrust for Level and Unaccelerated Flight calculation can be explained with given input values -> 100.005 = 99.99/(cos(0.01)).

FAQ

What is Thrust for Level and Unaccelerated Flight?
Thrust for Level and Unaccelerated Flight is the thrust acting on an aeroplane for zero acceleration and zero flight path angle and is represented as T = FD/(cos(σT)) or Thrust = Drag Force/(cos(Thrust angle)). Drag Force is the resisting force experienced by an object moving through a fluid & Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.
How to calculate Thrust for Level and Unaccelerated Flight?
Thrust for Level and Unaccelerated Flight is the thrust acting on an aeroplane for zero acceleration and zero flight path angle is calculated using Thrust = Drag Force/(cos(Thrust angle)). To calculate Thrust for Level and Unaccelerated Flight, you need Drag Force (FD) & Thrust angle T). With our tool, you need to enter the respective value for Drag Force & Thrust angle 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 Drag Force & Thrust angle. We can use 7 other way(s) to calculate the same, which is/are as follows -
  • 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+((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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