Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Parasite Drag Coefficient at zero lift
Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO
Lift for an unaccelerated flight
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO
Thrust angle for an unaccelerated flight for given lift
Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO
Thrust required for level, unaccelerated flight
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Dynamic pressure
Dynamic Pressure=Drag Force/(Drag Coefficient*Area) GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

9 Other formulas that calculate the same Output

Minimum Thrust required for given weight
Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Minimum Thrust required for given lift coefficient
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))) GO
Thrust for given liftoff distance
Thrust of an aircraft=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance) GO
Thrust in an accelerated flight
Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration)) GO
Minimum Thrust required
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift) GO
Thrust required for level, unaccelerated flight
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO
Thrust for a level, unaccelerated flight
Thrust of an aircraft=Drag Force/(cos(Thrust angle)) GO
Thrust required for given Lift-to-drag ratio
Thrust of an aircraft=Weight/Lift-to-drag ratio GO
Thrust required for given required power
Thrust of an aircraft=Power/Freestream Velocity GO

Thrust for given coefficients of lift and drag Formula

Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient
T=C<sub>D</sub>*W/C<sub>L</sub>
More formulas
Thrust required for level, unaccelerated flight GO
Lift for a level, unaccelerated flight at negligible thrust angle GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle GO
Thrust-to-weight ratio GO
Weight of aircraft for given coefficients of lift and drag GO
Coefficient of Lift for given thrust-to-weight ratio GO
Coefficient of Lift for given thrust and weight GO
Minimum Thrust required GO
Minimum Thrust required for given lift coefficient GO
Lift coefficient for given minimum required thrust GO
Minimum Thrust required for given weight GO

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 of an aircraft=Drag Coefficient*Weight/lift coefficient to calculate the Thrust of an aircraft, The Thrust for given coefficients of lift and drag is equal to coefficient of drag times weight of the aircraft divided by coefficient of lift. Thrust of an aircraft and 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 (W) and 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 -> 1000 = 100*100/10.

FAQ

What is Thrust for given coefficients of lift and drag?
The Thrust for given coefficients of lift and drag is equal to coefficient of drag times weight of the aircraft divided by coefficient of lift and is represented as T=CD*W/CL or Thrust of an aircraft=Drag Coefficient*Weight/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 is a vector quantity and defined as the product of mass and acceleration acting on that mass and The lift coefficient (CL) 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 equal to coefficient of drag times weight of the aircraft divided by coefficient of lift is calculated using Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient. To calculate Thrust for given coefficients of lift and drag, you need Drag Coefficient (CD), Weight (W) and lift coefficient (CL). With our tool, you need to enter the respective value for Drag Coefficient, Weight and 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 of an aircraft?
In this formula, Thrust of an aircraft uses Drag Coefficient, Weight and lift coefficient. We can use 9 other way(s) to calculate the same, which is/are as follows -
  • Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration))
  • Thrust of an aircraft=Drag Force/(cos(Thrust angle))
  • Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient
  • Thrust of an aircraft=Weight/Lift-to-drag ratio
  • Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift)
  • Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))
  • Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Thrust of an aircraft=Power/Freestream Velocity
  • Thrust of an aircraft=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)
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