FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Wing Area for given Yawing Moment Coefficient Formula

GoWing Area for given Moment Produced by Vertical Tail Formula

GoWing Area for given Vertical Tail Volume Ratio Formula

Fx Copy

LaTeX Copy

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. Check FAQs

S = 𝒍 v \cdot S v \cdot Q v \cdot C v \cdot \frac{β + σ}{C n \cdot b \cdot Q w}

S - Reference Area?𝒍_v - Vertical Tail Moment Arm?S_v - Vertical Tail Area?Q_v - Vertical Tail Dynamic Pressure?C_v - Vertical Tail Lift Curve Slope?β - Sideslip Angle?σ - Sidewash Angle?C_n - Yawing Moment Coefficient?b - Wingspan?Q_w - Wing Dynamic Pressure?

Wing Area for given Yawing Moment Coefficient Example

With values

With units

Only example

Here is how the Wing Area for given Yawing Moment Coefficient equation looks like with Values.

Here is how the Wing Area for given Yawing Moment Coefficient equation looks like with Units.

Here is how the Wing Area for given Yawing Moment Coefficient equation looks like.

5.087 = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{1.4 \cdot 1.15 \cdot 0.66}

5.087m² = 1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{1.4 \cdot 1.15m \cdot 0.66Pa}

5.087 = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{1.4 \cdot 1.15 \cdot 0.66}

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aircraft Mechanics » fx Wing Area for given Yawing Moment Coefficient

Wing Area for given Yawing Moment Coefficient Solution

Follow our step by step solution on how to calculate Wing Area for given Yawing Moment Coefficient?

FIRST Step Consider the formula

S = 𝒍 v \cdot S v \cdot Q v \cdot C v \cdot \frac{β + σ}{C n \cdot b \cdot Q w}

Next Step Substitute values of Variables

∴

S = 1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{1.4 \cdot 1.15m \cdot 0.66Pa}

Next Step Prepare to Evaluate

∴

S = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{1.4 \cdot 1.15 \cdot 0.66}

Next Step Evaluate

∴

S = 5.08695652173913m²

LAST Step Rounding Answer

∴

S = 5.087m²

Wing Area for given Yawing Moment Coefficient Formula Elements

Variables

Reference Area

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.

Symbol: S

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area

Vertical Tail Moment Arm

The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.

Symbol: 𝒍_v

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Vertical Tail Moment Arm

Vertical Tail Area

The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.

Symbol: S_v

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Vertical Tail Area

Vertical Tail Dynamic Pressure

Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.

Symbol: Q_v

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Vertical Tail Dynamic Pressure

Vertical Tail Lift Curve Slope

The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.

Symbol: C_v

Measurement: Reciprocal AngleUnit: rad⁻¹

Note: Value can be positive or negative.

Formulas to find Vertical Tail Lift Curve Slope

Sideslip Angle

The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.

Symbol: β

Measurement: AngleUnit: rad

Note: Value can be positive or negative.

Formulas to find Sideslip Angle

Sidewash Angle

Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.

Symbol: σ

Measurement: AngleUnit: rad

Note: Value can be positive or negative.

Formulas to find Sidewash Angle

Yawing Moment Coefficient

Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.

Symbol: C_n

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Yawing Moment Coefficient

Wingspan

The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

Symbol: b

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Wingspan

Wing Dynamic Pressure

Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.

Symbol: Q_w

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Wing Dynamic Pressure

Other Formulas to find Reference Area

Go Wing Area for given Moment Produced by Vertical Tail

S = \frac{N v}{C n \cdot Q w \cdot b}

Go Wing Area for given Vertical Tail Volume Ratio

S = 𝒍 v \cdot \frac{S v}{b \cdot V v}

Other formulas in Wing Tail Interaction category

Go Wing Dynamic Pressure for given Yawing Moment Coefficient

Q w = \frac{N v}{C n \cdot S \cdot b}

Go Wingspan for given Yawing Moment Coefficient

b = \frac{N v}{C n \cdot S \cdot Q w}

How to Evaluate Wing Area for given Yawing Moment Coefficient?

Wing Area for given Yawing Moment Coefficient evaluator uses Reference Area = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Yawing Moment Coefficient*Wingspan*Wing Dynamic Pressure) to evaluate the Reference Area, Wing Area for given Yawing Moment Coefficient is a calculation of the reference area required for directional stability, taking into account the vertical tail moment arm, area, and dynamic pressure, as well as the wing's lift curve slope, sideslip angle, and sidewash angle, all in relation to the yawing moment coefficient and wingspan, this formula is crucial in aerodynamics to ensure stable flight conditions. Reference Area is denoted by S symbol.

How to evaluate Wing Area for given Yawing Moment Coefficient using this online evaluator? To use this online evaluator for Wing Area for given Yawing Moment Coefficient, enter Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Yawing Moment Coefficient (C_n), Wingspan (b) & Wing Dynamic Pressure (Q_w) and hit the calculate button.

FAQs on Wing Area for given Yawing Moment Coefficient

What is the formula to find Wing Area for given Yawing Moment Coefficient?

The formula of Wing Area for given Yawing Moment Coefficient is expressed as Reference Area = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Yawing Moment Coefficient*Wingspan*Wing Dynamic Pressure). Here is an example- 5.086957 = 1.2*5*11*0.7*(0.05+0.067)/(1.4*1.15*0.66).

How to calculate Wing Area for given Yawing Moment Coefficient?

With Vertical Tail Moment Arm (𝒍_v), Vertical Tail Area (S_v), Vertical Tail Dynamic Pressure (Q_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Yawing Moment Coefficient (C_n), Wingspan (b) & Wing Dynamic Pressure (Q_w) we can find Wing Area for given Yawing Moment Coefficient using the formula - Reference Area = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Yawing Moment Coefficient*Wingspan*Wing Dynamic Pressure).

What are the other ways to Calculate Reference Area?

Here are the different ways to Calculate Reference Area-

Reference Area=Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan)
Reference Area=Vertical Tail Moment Arm*Vertical Tail Area/(Wingspan*Vertical Tail Volume Ratio)

Can the Wing Area for given Yawing Moment Coefficient be negative?

No, the Wing Area for given Yawing Moment Coefficient, measured in Area cannot be negative.

Which unit is used to measure Wing Area for given Yawing Moment Coefficient?

Wing Area for given Yawing Moment Coefficient is usually measured using the Square Meter[m²] for Area. Square Kilometer[m²], Square Centimeter[m²], Square Millimeter[m²] are the few other units in which Wing Area for given Yawing Moment Coefficient can be measured.

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Wing Area for given Yawing Moment Coefficient Formula

​GoWing Area for given Moment Produced by Vertical Tail Formula

​GoWing Area for given Vertical Tail Volume Ratio Formula

Wing Area for given Yawing Moment Coefficient Example

Wing Area for given Yawing Moment Coefficient Solution

Wing Area for given Yawing Moment Coefficient Formula Elements

Other Formulas to find Reference Area

Other formulas in Wing Tail Interaction category

How to Evaluate Wing Area for given Yawing Moment Coefficient?

FAQs on Wing Area for given Yawing Moment Coefficient

Variable Name

GoWing Area for given Moment Produced by Vertical Tail Formula

GoWing Area for given Vertical Tail Volume Ratio Formula