Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna 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
Drag in an accelerated flight
Drag Force=(Thrust of an aircraft*cos(Thrust angle))-(Mass*[g]*(sin(Flight path angle)))-(Mass*Acceleration) 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
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
Weight of aircraft in level, unaccelerated flight
Weight=Lift force+(Thrust of an aircraft*sin(Thrust angle)) GO
Drag for a level, unaccelerated flight
Drag Force=Thrust of an aircraft*(cos(Thrust angle)) 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

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 equation with coefficient of normal force
Drag Coefficient=coefficient of force*sin(Angle of attack) GO
Coefficient of Drag for given thrust-to-weight ratio
Drag Coefficient=lift coefficient*Thrust-to-weight ratio 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 and weight Formula

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

How can the thrust-to-weight ratio for launch vehicles be understood?

The thrust-to-weight ratio for a launch vehicle is numerically equal to the g-force that the vehicle can generate.

How to Calculate Coefficient of Drag for given thrust and weight?

Coefficient of Drag for given thrust and weight calculator uses Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight to calculate the Drag Coefficient, The Coefficient of Drag for given thrust and weight in a steady, level flight is given by the required thrust times coefficient of lift divided by the weight of aircraft. Drag Coefficient and is denoted by CD symbol.

How to calculate Coefficient of Drag for given thrust and weight using this online calculator? To use this online calculator for Coefficient of Drag for given thrust and weight, enter Thrust of an aircraft (T), lift coefficient (CL) and Weight (W) and hit the calculate button. Here is how the Coefficient of Drag for given thrust and weight calculation can be explained with given input values -> 10 = 100*10/100.

FAQ

What is Coefficient of Drag for given thrust and weight?
The Coefficient of Drag for given thrust and weight in a steady, level flight is given by the required thrust times coefficient of lift divided by the weight of aircraft and is represented as CD=T*CL/W or Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight. The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, 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 Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass.
How to calculate Coefficient of Drag for given thrust and weight?
The Coefficient of Drag for given thrust and weight in a steady, level flight is given by the required thrust times coefficient of lift divided by the weight of aircraft is calculated using Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight. To calculate Coefficient of Drag for given thrust and weight, you need Thrust of an aircraft (T), lift coefficient (CL) and Weight (W). With our tool, you need to enter the respective value for Thrust of an aircraft, lift coefficient and Weight 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 Thrust of an aircraft, lift coefficient and Weight. 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=lift coefficient*Thrust-to-weight ratio
  • 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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