Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions 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%
✖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%
✖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 given Vehicle Speed under Steady Flight Conditions [S]

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Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

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

Variables Used

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.
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.
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.
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
Lift Coefficient: 0.001 --> 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

S = 2*M_Aircraft*[g]/(ρ*C_l*V^2) --> 2*50000*[g]/(1.21*0.001*268^2)

Evaluating ... ...

S = 11284.0685863884

STEP 3: Convert Result to Output's Unit

11284.0685863884 Square Meter --> No Conversion Required

FINAL ANSWER

11284.0685863884 ≈ 11284.07 Square Meter <-- Aircraft Gross Wing Area

(Calculation completed in 00.014 seconds)

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Created by Mithila Muthamma PA

Coorg Institute of Technology (CIT), Coorg

Mithila Muthamma PA has created this Calculator and 2000+ more calculators!

Verified by M Naveen

National Institute of Technology (NIT), Warangal

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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)

Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions Formula

LaTeX Go

Aircraft Gross Wing Area = 2*Mass Aircraft*[g]/(Density Altitude for flying*Lift Coefficient*Vehicle Speed^2)
S = 2*M_Aircraft*[g]/(ρ*C_l*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 Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions?

Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions calculator uses Aircraft Gross Wing Area = 2*Mass Aircraft*[g]/(Density Altitude for flying*Lift Coefficient*Vehicle Speed^2) to calculate the Aircraft Gross Wing Area, The Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions is the surface area of a wing and is calculated by looking at the wing from a top-down view and measuring the area of the wing. This surface area is also known as the planform area. Aircraft Gross Wing Area is denoted by S symbol.

How to calculate Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions using this online calculator? To use this online calculator for Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions, enter Mass Aircraft (M_Aircraft), Density Altitude for flying (ρ), Lift Coefficient (C_l) & Vehicle Speed (V) and hit the calculate button. Here is how the Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions calculation can be explained with given input values -> 11284.07 = 2*50000*[g]/(1.21*0.001*74.4444444444444^2).

FAQ

What is Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions?

The Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions is the surface area of a wing and is calculated by looking at the wing from a top-down view and measuring the area of the wing. This surface area is also known as the planform area and is represented as S = 2*M_Aircraft*[g]/(ρ*C_l*V^2) or Aircraft Gross Wing Area = 2*Mass Aircraft*[g]/(Density Altitude for flying*Lift Coefficient*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, 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 & 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 Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions?

The Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions is the surface area of a wing and is calculated by looking at the wing from a top-down view and measuring the area of the wing. This surface area is also known as the planform area is calculated using Aircraft Gross Wing Area = 2*Mass Aircraft*[g]/(Density Altitude for flying*Lift Coefficient*Vehicle Speed^2). To calculate Aircraft Gross Wing Area given Vehicle Speed under Steady Flight Conditions, you need Mass Aircraft (M_Aircraft), Density Altitude for flying (ρ), Lift Coefficient (C_l) & Vehicle Speed (V). With our tool, you need to enter the respective value for Mass Aircraft, Density Altitude for flying, Lift Coefficient & Vehicle Speed 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 Aircraft Gross Wing Area?

In this formula, Aircraft Gross Wing Area uses Mass Aircraft, Density Altitude for flying, Lift Coefficient & Vehicle Speed. We can use 2 other way(s) to calculate the same, which is/are as follows -

Aircraft Gross Wing Area = Lifting Force of Aircraft/(0.5*Density Altitude for flying*Vehicle Speed^2*Lift Coefficient)
Aircraft Gross Wing Area = 2*Mass Aircraft*[g]/(Vehicle Speed^2*Density Altitude for flying*Maximum Lift Coefficient)

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