FormulaDen.com

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

Sidewash Angle given Yawing Moment Coefficient using Wingspan Formula

GoSidewash angle Formula

GoSidewash Angle for given Moment Produced by Vertical Tail Formula

Fx Copy

LaTeX Copy

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. Check FAQs

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

σ - Sidewash Angle?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?C_v - Vertical Tail Lift Curve Slope?β - Sideslip Angle?

Sidewash Angle given Yawing Moment Coefficient using Wingspan Example

With values

With units

Only example

Here is how the Sidewash Angle given Yawing Moment Coefficient using Wingspan equation looks like with Values.

Here is how the Sidewash Angle given Yawing Moment Coefficient using Wingspan equation looks like with Units.

Here is how the Sidewash Angle given Yawing Moment Coefficient using Wingspan equation looks like.

0.0668 = (1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 11 \cdot 0.7}) - 0.05

0.0668rad = (1.4 \cdot 5.08m² \cdot 1.15m \cdot \frac{0.66Pa}{1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹}) - 0.05rad

0.0668 = (1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 11 \cdot 0.7}) - 0.05

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 Sidewash Angle given Yawing Moment Coefficient using Wingspan

Sidewash Angle given Yawing Moment Coefficient using Wingspan Solution

Follow our step by step solution on how to calculate Sidewash Angle given Yawing Moment Coefficient using Wingspan?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

σ = (1.4 \cdot 5.08m² \cdot 1.15m \cdot \frac{0.66Pa}{1.2m \cdot 5m² \cdot 11Pa \cdot 0.7rad⁻¹}) - 0.05rad

Next Step Prepare to Evaluate

∴

σ = (1.4 \cdot 5.08 \cdot 1.15 \cdot \frac{0.66}{1.2 \cdot 5 \cdot 11 \cdot 0.7}) - 0.05

Next Step Evaluate

∴

σ = 0.06684rad

LAST Step Rounding Answer

∴

σ = 0.0668rad

Sidewash Angle given Yawing Moment Coefficient using Wingspan Formula Elements

Variables

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

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