Mean Aerodynamic Chord for Propeller-Driven Airplane Calculator

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✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Chord Length is the length of a line segment connecting any two points on the circumference of a circle.ⓘ Chord Length [L_c]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%

✖The Mean aerodynamic chord is a two-dimensional representation of the whole wing.ⓘ Mean Aerodynamic Chord for Propeller-Driven Airplane [c_ma]

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Formula

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Mean Aerodynamic Chord for Propeller-Driven Airplane

Formula

`"c"_{"ma"} = (1/"S")*int("L"_{"c"}^2,x,-"b"/2,"b"/2)`

Example

`"142.126m"=(1/"5.08m²")*int(("3.8m")^2,x,-"50m"/2,"50m"/2)`

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Mean Aerodynamic Chord for Propeller-Driven Airplane Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2)
c_ma = (1/S)*int(L_c^2,x,-b/2,b/2)
This formula uses 1 Functions, 4 Variables

Functions Used

int - The definite integral can be used to calculate net signed area, which is the area above the x -axis minus the area below the x -axis., int(expr, arg, from, to)

Variables Used

Mean aerodynamic chord - (Measured in Meter) - The Mean aerodynamic chord is a two-dimensional representation of the whole wing.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Chord Length - (Measured in Meter) - Chord Length is the length of a line segment connecting any two points on the circumference of a circle.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

STEP 1: Convert Input(s) to Base Unit

Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Chord Length: 3.8 Meter --> 3.8 Meter No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c_ma = (1/S)*int(L_c^2,x,-b/2,b/2) --> (1/5.08)*int(3.8^2,x,-50/2,50/2)

Evaluating ... ...

c_ma = 142.125984251969

STEP 3: Convert Result to Output's Unit

142.125984251969 Meter --> No Conversion Required

FINAL ANSWER

142.125984251969 ≈ 142.126 Meter <-- Mean aerodynamic chord

(Calculation completed in 00.004 seconds)

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< 18 Aircraft Dynamics Nomenclature Calculators

Sideslip angle

Go Sideslip Angle = asin(Velocity along pitch axis/(sqrt((Velocity along Roll Axis^2)+(Velocity along pitch axis^2)+(Velocity along yaw axis^2))))

Mean Aerodynamic Chord for Propeller-Driven Airplane

Go Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2)

Pitching moment coefficient

Go Pitching moment coefficient = Pitching moment/(Dynamic Pressure*Reference Area*Characteristic length)

Rolling moment coefficient

Go Rolling moment coefficient = Rolling moment/(Dynamic Pressure*Reference Area*Characteristic length)

Pitching moment

Go Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length

Yawing moment coefficient

Go Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length)

Rolling moment

Go Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length

Yawing moment

Go Yawing Moment = Yawing Moment Coefficient*Dynamic Pressure*Reference Area*Characteristic length

Normal force coefficient with aerodynamic normal force

Go Normal force coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area)

Aerodynamic normal force

Go Aerodynamic Normal Force = Normal force coefficient*Dynamic Pressure*Reference Area

Aerodynamic axial force

Go Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area

Side force coefficient

Go Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area)

Aerodynamic side force

Go Aerodynamic Side Force = Side force coefficient*Dynamic Pressure*Reference Area

Angle of attack

Go Angle of Attack = atan(Velocity along yaw axis/Velocity along Roll Axis)

Velocity along pitch axis for small sideslip angle

Go Velocity along pitch axis = Sideslip Angle*Velocity along Roll Axis

Velocity along roll axis for small sideslip angle

Go Velocity along Roll Axis = Velocity along pitch axis/Sideslip Angle

Velocity along roll axis for small angle of attack

Go Velocity along Roll Axis = Velocity along yaw axis/Angle of Attack

Velocity along yaw axis for small angle of attack

Go Velocity along yaw axis = Velocity along Roll Axis*Angle of Attack

Mean Aerodynamic Chord for Propeller-Driven Airplane Formula

Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2)
c_ma = (1/S)*int(L_c^2,x,-b/2,b/2)

How to find mean aerodynamic chord ?

The mean aerodynamic chord c is defined as the chord length that, when multiplied by the wing area, the dynamic pressure and the moment coefficient about the aerodynamic center, yields the value of the aerodynamic moment about the airplane's aerodynamic center.

How to Calculate Mean Aerodynamic Chord for Propeller-Driven Airplane?

Mean Aerodynamic Chord for Propeller-Driven Airplane calculator uses Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2) to calculate the Mean aerodynamic chord, The Mean Aerodynamic Chord for Propeller-Driven Airplane formula is defined as the chord length that, when multiplied by the wing area, the dynamic pressure,· and the moment coefficient about the aerodynamic center, yields the value of the aerodynamic moment about the airplane's aerodynamic center. Mean aerodynamic chord is denoted by c_ma symbol.

How to calculate Mean Aerodynamic Chord for Propeller-Driven Airplane using this online calculator? To use this online calculator for Mean Aerodynamic Chord for Propeller-Driven Airplane, enter Reference Area (S), Chord Length (L_c) & Wingspan (b) and hit the calculate button. Here is how the Mean Aerodynamic Chord for Propeller-Driven Airplane calculation can be explained with given input values -> 142.126 = (1/5.08)*int(3.8^2,x,-50/2,50/2).

FAQ

What is Mean Aerodynamic Chord for Propeller-Driven Airplane?

The Mean Aerodynamic Chord for Propeller-Driven Airplane formula is defined as the chord length that, when multiplied by the wing area, the dynamic pressure,· and the moment coefficient about the aerodynamic center, yields the value of the aerodynamic moment about the airplane's aerodynamic center and is represented as c_ma = (1/S)*int(L_c^2,x,-b/2,b/2) or Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2). The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, Chord Length is the length of a line segment connecting any two points on the circumference of a circle & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

How to calculate Mean Aerodynamic Chord for Propeller-Driven Airplane?

The Mean Aerodynamic Chord for Propeller-Driven Airplane formula is defined as the chord length that, when multiplied by the wing area, the dynamic pressure,· and the moment coefficient about the aerodynamic center, yields the value of the aerodynamic moment about the airplane's aerodynamic center is calculated using Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2). To calculate Mean Aerodynamic Chord for Propeller-Driven Airplane, you need Reference Area (S), Chord Length (L_c) & Wingspan (b). With our tool, you need to enter the respective value for Reference Area, Chord Length & Wingspan 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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