Minimum Thrust required for given lift coefficient Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Thrust Required for Level Unaccelerated Flight ↺

✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluidⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖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ⓘ Zero-lift drag coefficient [C_D,0]			+10% -10%
✖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%
✖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ⓘ Oswald efficiency factor [e]			+10% -10%
✖The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a wing [AR]			+10% -10%

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Minimum Thrust required for given lift coefficient [T]

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Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 200+ more calculators!

Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 200+ more calculators!

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Diagonal=sqrt(((Area)^2/(Breadth)^2)+(Breadth)^2) GO

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Side A=(Area*cosec(Angle Between Sides))/Side B GO

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Buoyant Force=Pressure*Area GO

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Perimeter=4*sqrt(Area) GO

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Breadth=Area/Length GO

Pressure when force and area are given

Pressure=Force/Area GO

Stress

Stress=Force/Area GO

< 9 Other formulas that calculate the same Output

Minimum Thrust required for given weight

Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Thrust for given liftoff distance

Thrust of an aircraft=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance) GO

Thrust in an accelerated flight

Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration)) GO

Minimum Thrust required

Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift) GO

Thrust for given coefficients of lift and drag

Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO

Thrust required for level, unaccelerated flight

Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO

Thrust for a level, unaccelerated flight

Thrust of an aircraft=Drag Force/(cos(Thrust angle)) GO

Thrust required for given Lift-to-drag ratio

Thrust of an aircraft=Weight/Lift-to-drag ratio GO

Thrust required for given required power

Thrust of an aircraft=Power/Freestream Velocity GO

Minimum Thrust required for given lift coefficient Formula

Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))
T=Pdynamic*A*(CD,0+((CL^2)/(pi*e*AR)))

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

Lift coefficient for given minimum required thrust GO

Minimum Thrust required for given weight GO

What are the factors for take-off thrust?

The factors for take-off thrust are runway length, runway elevation, runway slope, air temperature, wind speed, and minimum flight speed.

How to Calculate Minimum Thrust required for given lift coefficient?

Minimum Thrust required for given lift coefficient calculator uses Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))) to calculate the Thrust of an aircraft, The Minimum Thrust required for given lift coefficient in a steady, level flight is a function of the lift coefficient and the zero-lift drag coefficient of aircraft. Thrust of an aircraft and is denoted by T symbol.

How to calculate Minimum Thrust required for given lift coefficient using this online calculator? To use this online calculator for Minimum Thrust required for given lift coefficient, enter Dynamic Pressure (P_dynamic), Area (A), Zero-lift drag coefficient (C_D,0), lift coefficient (C_L), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Minimum Thrust required for given lift coefficient calculation can be explained with given input values -> 7965.797 = 10*50*(0.0161+((10^2)/(pi*0.5*4))).

FAQ

What is Minimum Thrust required for given lift coefficient?

The Minimum Thrust required for given lift coefficient in a steady, level flight is a function of the lift coefficient and the zero-lift drag coefficient of aircraft and is represented as T=P_{dynamic*A*(C_D,0+((C_L^2)/(pi*e*AR)))} or Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))). 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, 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, 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. , 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 and The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.

How to calculate Minimum Thrust required for given lift coefficient?

The Minimum Thrust required for given lift coefficient in a steady, level flight is a function of the lift coefficient and the zero-lift drag coefficient of aircraft is calculated using Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))). To calculate Minimum Thrust required for given lift coefficient, you need Dynamic Pressure (P_dynamic), Area (A), Zero-lift drag coefficient (C_D,0), lift coefficient (C_L), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Dynamic Pressure, Area, Zero-lift drag coefficient, lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing 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 Thrust of an aircraft?

In this formula, Thrust of an aircraft uses Dynamic Pressure, Area, Zero-lift drag coefficient, lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing. We can use 9 other way(s) to calculate the same, which is/are as follows -

Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration))
Thrust of an aircraft=Drag Force/(cos(Thrust angle))
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient
Thrust of an aircraft=Weight/Lift-to-drag ratio
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift)
Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing))
Thrust of an aircraft=Power/Freestream Velocity
Thrust of an aircraft=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)

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