Lift coefficient for given minimum required thrust Solution

STEP 0: Pre-Calculation Summary
Formula Used
Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))
CL = sqrt(pi*e*AR*((T/(Pdynamic*A))-CD,0))
This formula uses 1 Constants, 1 Functions, 7 Variables
Constants Used
pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288
Functions Used
sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)
Variables Used
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.
Oswald Efficiency Factor - The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio.
Aspect Ratio of a wing - The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
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.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Area - (Measured in Square Meter) - The area is the amount of two-dimensional space taken up by an object.
Zero Lift Drag Coefficient - Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
STEP 1: Convert Input(s) to Base Unit
Oswald Efficiency Factor: 0.51 --> No Conversion Required
Aspect Ratio of a wing: 4 --> No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area: 20 Square Meter --> 20 Square Meter No Conversion Required
Zero Lift Drag Coefficient: 0.31 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CL = sqrt(pi*e*AR*((T/(Pdynamic*A))-CD,0)) --> sqrt(pi*0.51*4*((100/(10*20))-0.31))
Evaluating ... ...
CL = 1.10348598202759
STEP 3: Convert Result to Output's Unit
1.10348598202759 --> No Conversion Required
FINAL ANSWER
1.10348598202759 1.103486 <-- Lift Coefficient
(Calculation completed in 00.004 seconds)

Credits

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

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

Lift coefficient for given minimum required thrust Formula

Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))
CL = sqrt(pi*e*AR*((T/(Pdynamic*A))-CD,0))

What is the condition for steady, level flight?

The loads acting on the aircraft should be in static equilibrium when the aircraft is in a steady, unaccelerated, level flight condition.

How to Calculate Lift coefficient for given minimum required thrust?

Lift coefficient for given minimum required thrust calculator uses Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)) to calculate the Lift Coefficient, The Lift coefficient for given minimum required thrust for a steady, level flight is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on lift. Lift Coefficient is denoted by CL symbol.

How to calculate Lift coefficient for given minimum required thrust using this online calculator? To use this online calculator for Lift coefficient for given minimum required thrust, enter Oswald Efficiency Factor (e), Aspect Ratio of a wing (AR), Thrust (T), Dynamic Pressure (Pdynamic), Area (A) & Zero Lift Drag Coefficient (CD,0) and hit the calculate button. Here is how the Lift coefficient for given minimum required thrust calculation can be explained with given input values -> 1.414058 = sqrt(pi*0.51*4*((100/(10*20))-0.31)).

FAQ

What is Lift coefficient for given minimum required thrust?
The Lift coefficient for given minimum required thrust for a steady, level flight is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on lift and is represented as CL = sqrt(pi*e*AR*((T/(Pdynamic*A))-CD,0)) or Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)). The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio, The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord, The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The area is the amount of two-dimensional space taken up by an object & Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
How to calculate Lift coefficient for given minimum required thrust?
The Lift coefficient for given minimum required thrust for a steady, level flight is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on lift is calculated using Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)). To calculate Lift coefficient for given minimum required thrust, you need Oswald Efficiency Factor (e), Aspect Ratio of a wing (AR), Thrust (T), Dynamic Pressure (Pdynamic), Area (A) & Zero Lift Drag Coefficient (CD,0). With our tool, you need to enter the respective value for Oswald Efficiency Factor, Aspect Ratio of a wing, Thrust, Dynamic Pressure, Area & Zero Lift Drag 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 Lift Coefficient?
In this formula, Lift Coefficient uses Oswald Efficiency Factor, Aspect Ratio of a wing, Thrust, Dynamic Pressure, Area & Zero Lift Drag Coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
  • Lift Coefficient = Weight of Body*Drag Coefficient/Thrust
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