Lifting Force Provided by Wing Body of Vehicle Calculator

✖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 [C_l]			+10% -10%

✖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 Provided by Wing Body of Vehicle [L_Aircraft]

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Lifting Force Provided by Wing Body of Vehicle Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

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
Lift Coefficient: 0.001 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

L_Aircraft = 0.5*ρ*V^2*S*C_l --> 0.5*1.21*268^2*23*0.001

Evaluating ... ...

L_Aircraft = 999.43096

STEP 3: Convert Result to Output's Unit

999430.96 Newton -->999.43096 Kilonewton (Check conversion here)

FINAL ANSWER

999.43096 ≈ 999.431 Kilonewton <-- Lifting Force of Aircraft

(Calculation completed in 00.004 seconds)

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Coorg Institute of Technology (CIT), Coorg

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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

Lifting Force Provided by Wing Body of Vehicle Formula

LaTeX Go

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

What is Maximum Structural Payload Weight ?

Maximum Structural Payload Weight (or mass) is the maximum demonstrated payload to be carried without stressing the aircraft fuselage. Maximum zero fuel weight (or mass) is the sum of the operating empty weight and the maximum structural payload weight.

what is lift coefficient in flights?

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

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

Lifting Force Provided by Wing Body of Vehicle calculator uses Lifting Force of Aircraft = 0.5*Density Altitude for flying*Vehicle Speed^2*Aircraft Gross Wing Area*Lift Coefficient to calculate the Lifting Force of Aircraft, Lifting Force Provided by Wing Body of Vehicle is perpendicular to the oncoming flow direction is defined as the total force provided by the wing body of the vehicle. Lifting Force of Aircraft is denoted by L_Aircraft symbol.

How to calculate Lifting Force Provided by Wing Body of Vehicle using this online calculator? To use this online calculator for Lifting Force Provided by Wing Body of Vehicle, enter Density Altitude for flying (ρ), Vehicle Speed (V), Aircraft Gross Wing Area (S) & Lift Coefficient (C_l) and hit the calculate button. Here is how the Lifting Force Provided by Wing Body of Vehicle calculation can be explained with given input values -> 0.999431 = 0.5*1.21*74.4444444444444^2*23*0.001.

FAQ

What is Lifting Force Provided by Wing Body of Vehicle?

Lifting Force Provided by Wing Body of Vehicle is perpendicular to the oncoming flow direction is defined as the total force provided by the wing body of the vehicle and is represented as L_Aircraft = 0.5*ρ*V^2*S*C_l or Lifting Force of Aircraft = 0.5*Density Altitude for flying*Vehicle Speed^2*Aircraft Gross Wing Area*Lift Coefficient. 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 & 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.

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

Lifting Force Provided by Wing Body of Vehicle is perpendicular to the oncoming flow direction is defined as the total force provided by the wing body of the vehicle is calculated using Lifting Force of Aircraft = 0.5*Density Altitude for flying*Vehicle Speed^2*Aircraft Gross Wing Area*Lift Coefficient. To calculate Lifting Force Provided by Wing Body of Vehicle, you need Density Altitude for flying (ρ), Vehicle Speed (V), Aircraft Gross Wing Area (S) & Lift Coefficient (C_l). With our tool, you need to enter the respective value for Density Altitude for flying, Vehicle Speed, Aircraft Gross Wing Area & Lift 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 Lifting Force of Aircraft?

In this formula, Lifting Force of Aircraft uses Density Altitude for flying, Vehicle Speed, Aircraft Gross Wing Area & Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Lifting Force of Aircraft = (((Mass Aircraft*[g]*cos(Angle between Runway and Horizontal Plane))-(Force of Friction/Coefficient of Rolling Friction)))

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