Thrust for given coefficients of lift and drag Solution

STEP 0: Pre-Calculation Summary
Formula Used
Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
T = CD*Wbody/CL
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.
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.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Lift Coefficient - The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
STEP 1: Convert Input(s) to Base Unit
Drag Coefficient: 0.5 --> No Conversion Required
Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
T = CD*Wbody/CL --> 0.5*221/1.1
Evaluating ... ...
T = 100.454545454545
STEP 3: Convert Result to Output's Unit
100.454545454545 Newton --> No Conversion Required
FINAL ANSWER
100.454545454545 100.4545 Newton <-- Thrust
(Calculation completed in 00.020 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!
Verified by Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V 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 given coefficients of lift and drag Formula

Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
T = CD*Wbody/CL

What are the parameters in determining the performance of an aircraft?

The thrust-to-weight ratio and wing loading are the two most important parameters in determining the performance of an aircraft.

How to Calculate Thrust for given coefficients of lift and drag?

Thrust for given coefficients of lift and drag calculator uses Thrust = Drag Coefficient*Weight of Body/Lift Coefficient to calculate the Thrust, The Thrust for given coefficients of lift and drag 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 for given coefficients of lift and drag using this online calculator? To use this online calculator for Thrust for given coefficients of lift and drag, enter Drag Coefficient (CD), Weight of Body (Wbody) & Lift Coefficient (CL) and hit the calculate button. Here is how the Thrust for given coefficients of lift and drag calculation can be explained with given input values -> 6027.273 = 0.5*221/1.1.

FAQ

What is Thrust for given coefficients of lift and drag?
The Thrust for given coefficients of lift and drag 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 = CD*Wbody/CL or Thrust = Drag Coefficient*Weight of Body/Lift 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, Weight of Body is the force acting on the object due to gravity & The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
How to calculate Thrust for given coefficients of lift and drag?
The Thrust for given coefficients of lift and drag 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 = Drag Coefficient*Weight of Body/Lift Coefficient. To calculate Thrust for given coefficients of lift and drag, you need Drag Coefficient (CD), Weight of Body (Wbody) & Lift Coefficient (CL). With our tool, you need to enter the respective value for Drag Coefficient, Weight of Body & Lift 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 Drag Coefficient, Weight of Body & Lift Coefficient. 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 = 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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