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

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Drag during Level Unaccelerated Flight ↺

✖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. ⓘ lift coefficient [C_L]			+10% -10%
✖Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engineⓘ Thrust-to-weight ratio [T/W]			+10% -10%

✖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ⓘ Coefficient of Drag for given thrust-to-weight ratio [C_D]

⎘ Copy

👎 Report Issue!

👍 Share Now!

You are here:

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 C_D 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 (C_L) 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 C_D=C_L*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 (C_L) 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)

Facebook
Twitter
WhatsApp
Reddit
LinkedIn
E-Mail

Let Others Know

✖

Facebook

Twitter

Copied!