Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

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
Non-dimensional pressure coefficient
Pressure coefficient=Change in static pressure/Dynamic Pressure GO
Moment coefficient
moment coefficient=moment/(Dynamic Pressure*Area*Chord Length) GO
Normal Force Coefficient
coefficient of force=Normal Force/(Dynamic Pressure*Area) GO
Velocity of Fluid When Dynamic Pressure is Given
Fluid Velocity=sqrt(Dynamic Pressure*2/Liquid Density) GO
Density of the Liquid When Dynamic Pressure is Given
Liquid Density=2*Dynamic Pressure/(Fluid Velocity^2) GO
Coefficient of drag
Drag Coefficient=Drag Force/(Dynamic Pressure*Area) GO
lift coefficient
lift coefficient=Lift force/(Dynamic Pressure*Area) GO
Axial force coefficient
coefficient of force=Force/(Dynamic Pressure*Area) GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

11 Other formulas that calculate the same Output

Total Lift Coefficient of wing-tail combination
lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area) GO
Lift Coefficient for a given turn rate
lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area) GO
Lift Coefficient for a given turn radius
lift coefficient=2*Weight/(Freestream density*Reference Area*[g]*Turn Radius) GO
lift coefficient for lift force in a body moving on a fluid
lift coefficient=Lift force/(Reference Area*0.5*Density*(Velocity^2)) GO
Lift Coefficient for a given wing loading and turn radius
lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g]) GO
Lift coefficient for a rotating cylinder with circulation
lift coefficient=Circulation/(Cylinder Radius*Freestream Velocity) GO
Coefficient of lift equation with angle of attack
lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack) GO
Coefficient of Lift for given thrust and weight
lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO
Coefficient of lift equation with coefficient of normal force
lift coefficient=coefficient of force*cos(Angle of attack) GO
Coefficient of Lift for given thrust-to-weight ratio
lift coefficient=Drag Coefficient/Thrust-to-weight ratio GO
lift coefficient
lift coefficient=Lift force/(Dynamic Pressure*Area) GO

Lift coefficient for given minimum required thrust Formula

lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient))
C<sub>L</sub>=sqrt(pi*e*AR*((T/(P<sub>dynamic*S))-C<sub>D,0</sub>))
More formulas
Thrust required for level, unaccelerated flight GO
Lift for a level, unaccelerated flight at negligible thrust angle GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle GO
Thrust-to-weight ratio GO
Thrust for given coefficients of lift and drag GO
Weight of aircraft for given coefficients of lift and drag GO
Coefficient of Lift for given thrust-to-weight ratio GO
Coefficient of Lift for given thrust and weight GO
Minimum Thrust required GO
Minimum Thrust required for given lift coefficient GO
Minimum Thrust required for given weight GO

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 of an aircraft/(Dynamic Pressure*Reference 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 function of the zero-lift drag coefficient of the aircraft. lift coefficient and 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 of an aircraft (T), Dynamic Pressure (Pdynamic), Reference Area (S) and 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 -> 3.530611 = sqrt(pi*0.5*4*((100/(10*5))-0.0161)).

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 function of the zero-lift drag coefficient of the aircraft and is represented as CL=sqrt(pi*e*AR*((T/(Pdynamic*S))-CD,0)) or lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference 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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area and The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude.
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 function of the zero-lift drag coefficient of the aircraft is calculated using lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference 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 of an aircraft (T), Dynamic Pressure (Pdynamic), Reference Area (S) and 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 of an aircraft, Dynamic Pressure, Reference Area and 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 of an aircraft, Dynamic Pressure, Reference Area and Zero-lift drag coefficient. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • lift coefficient=Lift force/(Dynamic Pressure*Area)
  • lift coefficient=Drag Coefficient/Thrust-to-weight ratio
  • lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft
  • lift coefficient=coefficient of force*cos(Angle of attack)
  • lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack)
  • lift coefficient=2*Weight/(Freestream density*Reference Area*[g]*Turn Radius)
  • lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
  • lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g])
  • lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
  • lift coefficient=Lift force/(Reference Area*0.5*Density*(Velocity^2))
  • lift coefficient=Circulation/(Cylinder Radius*Freestream Velocity)
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