Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
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 100+ 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
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Coefficient of Lift for given thrust-to-weight ratio
lift coefficient=Drag Coefficient/Thrust-to-weight ratio GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient GO

11 Other formulas that calculate the same Output

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
Drag coefficient of flat plate laminar flow given Schmidt number
Drag Coefficient=(2*Convective mass transfer coefficient*(Schmidt Number^0.67))/Free stream velocity GO
Coefficient of drag equation using energy released from blast wave
Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter ) GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO
Coefficient of drag equation with coefficient of normal force
Drag Coefficient=coefficient of force*sin(Angle of attack) GO
Coefficient of drag
Drag Coefficient=Drag Force/(Dynamic Pressure*Area) GO
Drag coefficient of flat plate in combined laminar turbulent flow
Drag Coefficient=0.0571/(Reynolds Number^0.2) GO
Drag coefficient of flat plate laminar flow
Drag Coefficient=0.644/(Reynolds Number^0.5) GO
Coefficient of drag equation with angle of attack
Drag Coefficient=2*(sin(Angle of attack))^3 GO
drag coefficient of flat plate laminar flow given friction factor
Drag Coefficient=Friction factor/4 GO

Coefficient of Drag for given thrust-to-weight ratio Formula

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

What does a thrust-to-weight ratio greater than one mean?

Aircraft with a thrust-to-weight ratio greater than 1:1 can pitch straight up and maintain airspeed until performance decreases at higher altitudes.

How to Calculate Coefficient of Drag for given thrust-to-weight ratio?

Coefficient of Drag for given thrust-to-weight ratio calculator uses Drag Coefficient=lift coefficient*Thrust-to-weight ratio to calculate the Drag Coefficient, The Coefficient of Drag for given thrust-to-weight ratio is given by the product of the coefficient of lift and thrust-to-weight ratio of the aircraft. Drag Coefficient and is denoted by CD symbol.

How to calculate Coefficient of Drag for given thrust-to-weight ratio using this online calculator? To use this online calculator for Coefficient of Drag for given thrust-to-weight ratio, enter lift coefficient (CL) and Thrust-to-weight ratio (T/W) and hit the calculate button. Here is how the Coefficient of Drag for given thrust-to-weight ratio calculation can be explained with given input values -> 600 = 10*60.

FAQ

What is Coefficient of Drag for given thrust-to-weight ratio?
The Coefficient of Drag for given thrust-to-weight ratio is given by the product of the coefficient of lift and thrust-to-weight ratio of the aircraft and is represented as CD=CL*T/W or Drag Coefficient=lift coefficient*Thrust-to-weight ratio. 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. and Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.
How to calculate Coefficient of Drag for given thrust-to-weight ratio?
The Coefficient of Drag for given thrust-to-weight ratio is given by the product of the coefficient of lift and thrust-to-weight ratio of the aircraft is calculated using Drag Coefficient=lift coefficient*Thrust-to-weight ratio. To calculate Coefficient of Drag for given thrust-to-weight ratio, you need lift coefficient (CL) and Thrust-to-weight ratio (T/W). With our tool, you need to enter the respective value for lift coefficient and Thrust-to-weight ratio 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 Drag Coefficient?
In this formula, Drag Coefficient uses lift coefficient and Thrust-to-weight ratio. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • Drag Coefficient=Drag Force/(Dynamic Pressure*Area)
  • Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight
  • Drag Coefficient=coefficient of force*sin(Angle of attack)
  • Drag Coefficient=2*(sin(Angle of attack))^3
  • Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter )
  • Drag Coefficient=0.644/(Reynolds Number^0.5)
  • Drag Coefficient=(2*Convective mass transfer coefficient*(Schmidt Number^0.67))/Free stream velocity
  • Drag Coefficient=Friction factor/4
  • Drag Coefficient=0.0571/(Reynolds Number^0.2)
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