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Dynamic Pressure at Wing for given Yawing Moment Coefficient Formula

GoWing Dynamic Pressure for given Yawing Moment Coefficient Formula

GoDynamic Pressure at Wing for given Vertical Tail Efficiency Formula

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

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

Q_w - Wing Dynamic Pressure?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?S - Reference Area?b - Wingspan?C_n - Yawing Moment Coefficient?

Dynamic Pressure at Wing for given Yawing Moment Coefficient Example

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

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

Here is how the Dynamic Pressure at Wing for given Yawing Moment Coefficient equation looks like.

0.6609 = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 1.4}

0.6609Pa = 1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{5.08m² \cdot 1.15m \cdot 1.4}

0.6609 = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 1.4}

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Dynamic Pressure at Wing for given Yawing Moment Coefficient Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

Q w = 1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹ \cdot \frac{0.05rad + 0.067rad}{5.08m² \cdot 1.15m \cdot 1.4}

Next Step Prepare to Evaluate

∴

Q w = 1.2 \cdot 5 \cdot 11 \cdot 0.7 \cdot \frac{0.05 + 0.067}{5.08 \cdot 1.15 \cdot 1.4}

Next Step Evaluate

∴

Q w = 0.66090380006847Pa

LAST Step Rounding Answer

∴

Q w = 0.6609Pa

Dynamic Pressure at Wing for given Yawing Moment Coefficient Formula Elements

Variables

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

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

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

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

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

Other Formulas to find Wing Dynamic Pressure

Go Wing Dynamic Pressure for given Yawing Moment Coefficient

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

Go Dynamic Pressure at Wing for given Vertical Tail Efficiency

Q w = \frac{Q v}{η v}

Other formulas in Wing Tail Interaction category

Go Wing Area for given Moment Produced by Vertical Tail

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

Go Wingspan for given Yawing Moment Coefficient

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

How to Evaluate Dynamic Pressure at Wing for given Yawing Moment Coefficient?

Dynamic Pressure at Wing for given Yawing Moment Coefficient evaluator uses Wing Dynamic Pressure = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Yawing Moment Coefficient) to evaluate the Wing Dynamic Pressure, Dynamic Pressure at Wing for given Yawing Moment Coefficient is a measure of the pressure exerted on an aircraft wing due to its velocity, taking into account the vertical tail's moment arm, area and lift curve slope, as well as the sideslip and sidewash angles, referenced to the wing's span and directional stability. Wing Dynamic Pressure is denoted by Q_w symbol.

How to evaluate Dynamic Pressure at Wing for given Yawing Moment Coefficient using this online evaluator? To use this online evaluator for Dynamic Pressure at Wing 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), Reference Area (S), Wingspan (b) & Yawing Moment Coefficient (C_n) and hit the calculate button.

FAQs on Dynamic Pressure at Wing for given Yawing Moment Coefficient

What is the formula to find Dynamic Pressure at Wing for given Yawing Moment Coefficient?

The formula of Dynamic Pressure at Wing for given Yawing Moment Coefficient is expressed as Wing Dynamic Pressure = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Yawing Moment Coefficient). Here is an example- 0.659241 = 1.2*5*11*0.7*(0.05+0.067)/(5.08*1.15*1.4).

How to calculate Dynamic Pressure at Wing 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), Reference Area (S), Wingspan (b) & Yawing Moment Coefficient (C_n) we can find Dynamic Pressure at Wing for given Yawing Moment Coefficient using the formula - Wing Dynamic Pressure = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Yawing Moment Coefficient).

What are the other ways to Calculate Wing Dynamic Pressure?

Here are the different ways to Calculate Wing Dynamic Pressure-

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

Can the Dynamic Pressure at Wing for given Yawing Moment Coefficient be negative?

No, the Dynamic Pressure at Wing for given Yawing Moment Coefficient, measured in Pressure cannot be negative.

Which unit is used to measure Dynamic Pressure at Wing for given Yawing Moment Coefficient?

Dynamic Pressure at Wing for given Yawing Moment Coefficient is usually measured using the Pascal[Pa] for Pressure. Kilopascal[Pa], Bar[Pa], Pound Per Square Inch[Pa] are the few other units in which Dynamic Pressure at Wing for given Yawing Moment Coefficient can be measured.

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Dynamic Pressure at Wing for given Yawing Moment Coefficient Formula

​GoWing Dynamic Pressure for given Yawing Moment Coefficient Formula

​GoDynamic Pressure at Wing for given Vertical Tail Efficiency Formula

Dynamic Pressure at Wing for given Yawing Moment Coefficient Example

Dynamic Pressure at Wing for given Yawing Moment Coefficient Solution

Dynamic Pressure at Wing for given Yawing Moment Coefficient Formula Elements

Other Formulas to find Wing Dynamic Pressure

Other formulas in Wing Tail Interaction category

How to Evaluate Dynamic Pressure at Wing for given Yawing Moment Coefficient?

FAQs on Dynamic Pressure at Wing for given Yawing Moment Coefficient

Variable Name

GoWing Dynamic Pressure for given Yawing Moment Coefficient Formula

GoDynamic Pressure at Wing for given Vertical Tail Efficiency Formula