Coefficient of Drag for given thrust and weight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Drag Coefficient = Thrust*Lift Coefficient/Weight of Body
CD = T*CL/Wbody
This formula uses 4 Variables
Variables Used
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.
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.
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.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
STEP 1: Convert Input(s) to Base Unit
Thrust: 100 Newton --> 100 Newton No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Weight of Body: 221 Newton --> 221 Newton No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CD = T*CL/Wbody --> 100*1.1/221
Evaluating ... ...
CD = 0.497737556561086
STEP 3: Convert Result to Output's Unit
0.497737556561086 --> No Conversion Required
FINAL ANSWER
0.497737556561086 0.497738 <-- Drag Coefficient
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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Verified by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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19 Lift and Drag Requirements Calculators

Lift coefficient for given minimum required thrust
Go Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))
Zero-lift drag coefficient for given lift coefficient
Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
Zero-lift drag coefficient at minimum required thrust
Go Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
Lift-induced drag coefficient for given required thrust
Go Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
Zero-lift drag coefficient for given required thrust
Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
Lift for Unaccelerated Flight
Go Lift Force = Weight of Body-Thrust*sin(Thrust angle)
Coefficient of Drag for given thrust and weight
Go Drag Coefficient = Thrust*Lift Coefficient/Weight of Body
Coefficient of Lift for given thrust and weight
Go Lift Coefficient = Weight of Body*Drag Coefficient/Thrust
Drag for Level and Unaccelerated Flight at Negligible Thrust Angle
Go Drag Force = Dynamic Pressure*Area*Drag Coefficient
Lift for Level and Unaccelerated Flight at Negligible Thrust Angle
Go Lift Force = Dynamic Pressure*Area*Lift Coefficient
Drag for Level and Unaccelerated Flight
Go Drag Force = Thrust*(cos(Thrust angle))
Coefficient of Drag for given thrust-to-weight ratio
Go Drag Coefficient = Lift Coefficient*Thrust-to-Weight Ratio
Coefficient of Lift for given thrust-to-weight ratio
Go Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
Lift-to-drag ratio for given required thrust of aircraft
Go Lift-to-drag Ratio = Weight of Body/Thrust
Freestream Velocity for given total drag force
Go Freestream Velocity = Power/Drag Force
Total drag force for given required power
Go Drag Force = Power/Freestream Velocity
Freestream velocity for given required power
Go Freestream Velocity = Power/Thrust
Coefficient of Drag due to lift for minimum power required
Go Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient
Zero-lift drag coefficient for minimum power required
Go Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

Coefficient of Drag for given thrust and weight Formula

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

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*Lift Coefficient/Weight of Body 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 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 (T), Lift Coefficient (CL) & Weight of Body (Wbody) 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 -> 0.497738 = 100*1.1/221.

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/Wbody or Drag Coefficient = Thrust*Lift Coefficient/Weight of Body. The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, 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 & Weight of Body is the force acting on the object due to gravity.
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*Lift Coefficient/Weight of Body. To calculate Coefficient of Drag for given thrust and weight, you need Thrust (T), Lift Coefficient (CL) & Weight of Body (Wbody). With our tool, you need to enter the respective value for Thrust, Lift Coefficient & Weight of Body 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, Lift Coefficient & Weight of Body. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Drag Coefficient = Lift Coefficient*Thrust-to-Weight Ratio
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