Maximum Attainable Lift Coefficient given Vehicle Stalling Speed Calculator

✖Mass Aircraft is the quantity of matter in a body regardless of its volume or of any forces acting on it.ⓘ Mass Aircraft [M_Aircraft]			+10% -10%
✖Density Altitude for flying is a representation of the amount of mass of a substance, material or object in relation to the space it occupies at an altitude.ⓘ Density Altitude for flying [ρ]			+10% -10%
✖Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing.ⓘ Aircraft Gross Wing Area [S]			+10% -10%
✖Vehicle Speed (True Air Speed) of an aircraft is the speed of aircraft relative to air mass through which it is flying. The true airspeed is important information for accurate navigation of aircraft.ⓘ Vehicle Speed [V]			+10% -10%

✖Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.ⓘ Maximum Attainable Lift Coefficient given Vehicle Stalling Speed [C_L,max]

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Maximum Attainable Lift Coefficient given Vehicle Stalling Speed Solution

STEP 0: Pre-Calculation Summary

Formula Used

Maximum Lift Coefficient = 2*Mass Aircraft*[g]/(Density Altitude for flying*Aircraft Gross Wing Area*Vehicle Speed^2)
C_L,max = 2*M_Aircraft*[g]/(ρ*S*V^2)
This formula uses 1 Constants, 5 Variables

Constants Used

[g] - Gravitational acceleration on Earth Value Taken As 9.80665

Variables Used

Maximum Lift Coefficient - Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.
Mass Aircraft - (Measured in Kilogram) - Mass Aircraft is the quantity of matter in a body regardless of its volume or of any forces acting on it.
Density Altitude for flying - (Measured in Kilogram per Cubic Meter) - Density Altitude for flying is a representation of the amount of mass of a substance, material or object in relation to the space it occupies at an altitude.
Aircraft Gross Wing Area - (Measured in Square Meter) - Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing.
Vehicle Speed - (Measured in Kilometer per Hour) - Vehicle Speed (True Air Speed) of an aircraft is the speed of aircraft relative to air mass through which it is flying. The true airspeed is important information for accurate navigation of aircraft.

STEP 1: Convert Input(s) to Base Unit

Mass Aircraft: 50000 Kilogram --> 50000 Kilogram No Conversion Required
Density Altitude for flying: 1.21 Kilogram per Cubic Meter --> 1.21 Kilogram per Cubic Meter No Conversion Required
Aircraft Gross Wing Area: 23 Square Meter --> 23 Square Meter No Conversion Required
Vehicle Speed: 268 Kilometer per Hour --> 268 Kilometer per Hour No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L,max = 2*M_Aircraft*[g]/(ρ*S*V^2) --> 2*50000*[g]/(1.21*23*268^2)

Evaluating ... ...

C_L,max = 0.490611677669061

STEP 3: Convert Result to Output's Unit

0.490611677669061 --> No Conversion Required

FINAL ANSWER

0.490611677669061 ≈ 0.490612 <-- Maximum Lift Coefficient

(Calculation completed in 00.004 seconds)

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< Aircraft Gross Wing Calculators

Vehicle Stalling Speed given Maximum Attainable Lift Coefficient

LaTeX Go Vehicle Speed = sqrt((2*Mass Aircraft*[g])/(Density Altitude for flying*Aircraft Gross Wing Area*Maximum Lift Coefficient))

Maximum Attainable Lift Coefficient given Vehicle Stalling Speed

LaTeX Go Maximum Lift Coefficient = 2*Mass Aircraft*[g]/(Density Altitude for flying*Aircraft Gross Wing Area*Vehicle Speed^2)

Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions

LaTeX Go Aircraft Gross Wing Area = 2*Mass Aircraft*[g]/(Density Altitude for flying*Lift Coefficient*Vehicle Speed^2)

Aircraft Gross Wing Area for Lifting Force Provided by Wing Body of Vehicle

LaTeX Go Aircraft Gross Wing Area = Lifting Force of Aircraft/(0.5*Density Altitude for flying*Vehicle Speed^2*Lift Coefficient)

Maximum Attainable Lift Coefficient given Vehicle Stalling Speed Formula

LaTeX Go

Maximum Lift Coefficient = 2*Mass Aircraft*[g]/(Density Altitude for flying*Aircraft Gross Wing Area*Vehicle Speed^2)
C_L,max = 2*M_Aircraft*[g]/(ρ*S*V^2)

What is Lift Force?

Lift is the force that directly opposes the weight of an airplane and holds the airplane in the air. Lift is a mechanical aerodynamic force produced by the motion of the airplane through the air. Because lift is a force, it is a vector quantity, having both a magnitude and a direction associated with it.

How to Calculate Maximum Attainable Lift Coefficient given Vehicle Stalling Speed?

Maximum Attainable Lift Coefficient given Vehicle Stalling Speed calculator uses Maximum Lift Coefficient = 2*Mass Aircraft*[g]/(Density Altitude for flying*Aircraft Gross Wing Area*Vehicle Speed^2) to calculate the Maximum Lift Coefficient, The Maximum Attainable Lift Coefficient given Vehicle Stalling Speed is the maximum number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift. Maximum Lift Coefficient is denoted by C_L,max symbol.

How to calculate Maximum Attainable Lift Coefficient given Vehicle Stalling Speed using this online calculator? To use this online calculator for Maximum Attainable Lift Coefficient given Vehicle Stalling Speed, enter Mass Aircraft (M_Aircraft), Density Altitude for flying (ρ), Aircraft Gross Wing Area (S) & Vehicle Speed (V) and hit the calculate button. Here is how the Maximum Attainable Lift Coefficient given Vehicle Stalling Speed calculation can be explained with given input values -> 0.490612 = 2*50000*[g]/(1.21*23*74.4444444444444^2).

FAQ

What is Maximum Attainable Lift Coefficient given Vehicle Stalling Speed?

The Maximum Attainable Lift Coefficient given Vehicle Stalling Speed is the maximum number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift and is represented as C_L,max = 2*M_Aircraft*[g]/(ρ*S*V^2) or Maximum Lift Coefficient = 2*Mass Aircraft*[g]/(Density Altitude for flying*Aircraft Gross Wing Area*Vehicle Speed^2). Mass Aircraft is the quantity of matter in a body regardless of its volume or of any forces acting on it, Density Altitude for flying is a representation of the amount of mass of a substance, material or object in relation to the space it occupies at an altitude, Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing & Vehicle Speed (True Air Speed) of an aircraft is the speed of aircraft relative to air mass through which it is flying. The true airspeed is important information for accurate navigation of aircraft.

How to calculate Maximum Attainable Lift Coefficient given Vehicle Stalling Speed?

The Maximum Attainable Lift Coefficient given Vehicle Stalling Speed is the maximum number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift is calculated using Maximum Lift Coefficient = 2*Mass Aircraft*[g]/(Density Altitude for flying*Aircraft Gross Wing Area*Vehicle Speed^2). To calculate Maximum Attainable Lift Coefficient given Vehicle Stalling Speed, you need Mass Aircraft (M_Aircraft), Density Altitude for flying (ρ), Aircraft Gross Wing Area (S) & Vehicle Speed (V). With our tool, you need to enter the respective value for Mass Aircraft, Density Altitude for flying, Aircraft Gross Wing Area & Vehicle Speed and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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