Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Calculator

✖Lifting Force of Aircraft provided by the wing-body of the vehicle. Lift is defined as the component of the aerodynamic force that is perpendicular to the flow direction.ⓘ Lifting Force of Aircraft [L_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%
✖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%
✖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%

✖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.ⓘ Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle [C_l]

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Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area)
C_l = L_Aircraft/(0.5*ρ*(V^2)*S)
This formula uses 5 Variables

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.
Lifting Force of Aircraft - (Measured in Kilonewton) - Lifting Force of Aircraft provided by the wing-body of the vehicle. Lift is defined as the component of the aerodynamic force that is perpendicular to the flow direction.
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.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Lifting Force of Aircraft: 1072.39 Kilonewton --> 1072.39 Kilonewton No Conversion Required
Density Altitude for flying: 1.21 Kilogram per Cubic Meter --> 1.21 Kilogram per Cubic Meter No Conversion Required
Vehicle Speed: 268 Kilometer per Hour --> 268 Kilometer per Hour No Conversion Required
Aircraft Gross Wing Area: 23 Square Meter --> 23 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_l = L_Aircraft/(0.5*ρ*(V^2)*S) --> 1072.39/(0.5*1.21*(268^2)*23)

Evaluating ... ...

C_l = 0.00107300058025019

STEP 3: Convert Result to Output's Unit

0.00107300058025019 --> No Conversion Required

FINAL ANSWER

0.00107300058025019 ≈ 0.001073 <-- Lift Coefficient

(Calculation completed in 00.004 seconds)

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< Aircraft Runway Length Estimation Calculators

Operating Empty Weight when Desired Take-off Weight is considered

LaTeX Go Operating Empty Weight = Desired Takeoff Weight of Aircraft-Payload Carried-Fuel Weight to be carried

Payload carried when desired take-off weight is considered

LaTeX Go Payload Carried = Desired Takeoff Weight of Aircraft-Operating Empty Weight-Fuel Weight to be carried

Fuel Weight to be Carried given Desired Takeoff Weight

LaTeX Go Fuel Weight to be carried = Desired Takeoff Weight of Aircraft-Payload Carried-Operating Empty Weight

Desired Take off Weight

LaTeX Go Desired Takeoff Weight of Aircraft = Payload Carried+Operating Empty Weight+Fuel Weight to be carried

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Formula

LaTeX Go

Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area)
C_l = L_Aircraft/(0.5*ρ*(V^2)*S)

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.

What is 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. A lifting body is a foil or a complete foil-bearing body such as a fixed-wing aircraft.

How to Calculate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle calculator uses Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area) to calculate the Lift Coefficient, Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle 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 C_l symbol.

How to calculate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle using this online calculator? To use this online calculator for Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle, enter Lifting Force of Aircraft (L_Aircraft), Density Altitude for flying (ρ), Vehicle Speed (V) & Aircraft Gross Wing Area (S) and hit the calculate button. Here is how the Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle calculation can be explained with given input values -> 0.001073 = 1072390/(0.5*1.21*(74.4444444444444^2)*23).

FAQ

What is Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle 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 C_l = L_Aircraft/(0.5*ρ*(V^2)*S) or Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area). Lifting Force of Aircraft provided by the wing-body of the vehicle. Lift is defined as the component of the aerodynamic force that is perpendicular to the flow direction, 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, 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 & Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing.

How to calculate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle 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 = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area). To calculate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle, you need Lifting Force of Aircraft (L_Aircraft), Density Altitude for flying (ρ), Vehicle Speed (V) & Aircraft Gross Wing Area (S). With our tool, you need to enter the respective value for Lifting Force of Aircraft, Density Altitude for flying, Vehicle Speed & Aircraft Gross Wing Area 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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