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Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Formula

GoVertical Tail Lift Curve Slope Formula

GoVertical Tail Lift Curve Slope for Given Moment Formula

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

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

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

Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Example

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Here is how the Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient equation looks like with Values.

Here is how the Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient equation looks like with Units.

Here is how the Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient equation looks like.

0.699 = 1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 11 \cdot (0.05 + 0.067)}

0.699rad⁻¹ = 1.4 \cdot 5.08m² \cdot 1.15m \cdot \frac{0.66Pa}{1.2m \cdot 5m² \cdot 11Pa \cdot (0.05rad + 0.067rad)}

0.699 = 1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 11 \cdot (0.05 + 0.067)}

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Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Solution

Follow our step by step solution on how to calculate Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

C v = 1.4 \cdot 5.08m² \cdot 1.15m \cdot \frac{0.66Pa}{1.2m \cdot 5m² \cdot 11Pa \cdot (0.05rad + 0.067rad)}

Next Step Prepare to Evaluate

∴

C v = 1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 11 \cdot (0.05 + 0.067)}

Next Step Evaluate

∴

C v = 0.699042735042735rad⁻¹

LAST Step Rounding Answer

∴

C v = 0.699rad⁻¹

Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient Formula Elements

Variables

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

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

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