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Deflection Angle given Lift Coefficient Formula

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The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position. Check FAQs

δ a = \frac{C l}{C lα \cdot τ}

δ_a - Deflection of Aileron?C_l - Lift Coefficient Roll Control?C_lα - Lift Coefficient Slope Roll Control?τ - Flap Effectiveness Parameter?

Deflection Angle given Lift Coefficient Example

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Here is how the Deflection Angle given Lift Coefficient equation looks like with Values.

Here is how the Deflection Angle given Lift Coefficient equation looks like with Units.

Here is how the Deflection Angle given Lift Coefficient equation looks like.

5.5303 = \frac{0.073}{0.02 \cdot 0.66}

5.5303rad = \frac{0.073}{0.02 \cdot 0.66}

5.5303 = \frac{0.073}{0.02 \cdot 0.66}

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Deflection Angle given Lift Coefficient Solution

Follow our step by step solution on how to calculate Deflection Angle given Lift Coefficient?

FIRST Step Consider the formula

δ a = \frac{C l}{C lα \cdot τ}

Next Step Substitute values of Variables

∴

δ a = \frac{0.073}{0.02 \cdot 0.66}

Next Step Prepare to Evaluate

∴

δ a = \frac{0.073}{0.02 \cdot 0.66}

Next Step Evaluate

∴

δ a = 5.53030303030303rad

LAST Step Rounding Answer

∴

δ a = 5.5303rad

Deflection Angle given Lift Coefficient Formula Elements

Variables

Deflection of Aileron

The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position.

Symbol: δ_a

Measurement: AngleUnit: rad

Note: Value can be positive or negative.

Formulas to find Deflection of Aileron

Lift Coefficient Roll Control

The Lift Coefficient Roll Control is a dimensionless quantity that shows how much lift a lifting body creates relative to the fluid density, velocity, and an associated reference area.

Symbol: C_l

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Lift Coefficient Roll Control

Lift Coefficient Slope Roll Control

Lift Coefficient Slope Roll Control with respect to the angle of attack (alpha). It's a crucial parameter that helps determine the effectiveness of ailerons in rolling an aircraft.

Symbol: C_lα

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Lift Coefficient Slope Roll Control

Flap Effectiveness Parameter

The Flap Effectiveness Parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.

Symbol: τ

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Flap Effectiveness Parameter

Other formulas in Lateral Control category

Go Aileron Section lift Coefficient given Aileron Deflection

C l = C lα \cdot (\frac{dα}{dδ a}) \cdot δ a

Go Aileron Deflection given Aileron Lift Coefficient

C l = \frac{2 \cdot C lαw \cdot τ \cdot δ a}{S \cdot b} \cdot \int (c \cdot x, x, y 1, y 2)

Go Aileron Control Effectiveness given Aileron Deflection

τ = \frac{C l}{C lα \cdot δ a}

Go Roll Control Power

Cl δα = \frac{2 \cdot C lαw \cdot τ}{S \cdot b} \cdot \int (c \cdot x, x, y 1, y 2)

How to Evaluate Deflection Angle given Lift Coefficient?

Deflection Angle given Lift Coefficient evaluator uses Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter) to evaluate the Deflection of Aileron, The Deflection Angle given Lift Coefficient formula calculates the angle at which the aileron is positioned relative to its neutral or zero position, this angle determines the amount of lift differential between the wings, which in turn controls the roll motion of the aircraft. Deflection of Aileron is denoted by δ_a symbol.

How to evaluate Deflection Angle given Lift Coefficient using this online evaluator? To use this online evaluator for Deflection Angle given Lift Coefficient, enter Lift Coefficient Roll Control (C_l), Lift Coefficient Slope Roll Control (C_lα) & Flap Effectiveness Parameter (τ) and hit the calculate button.

FAQs on Deflection Angle given Lift Coefficient

What is the formula to find Deflection Angle given Lift Coefficient?

The formula of Deflection Angle given Lift Coefficient is expressed as Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter). Here is an example- 5.530303 = 0.073/(0.02*0.66).

How to calculate Deflection Angle given Lift Coefficient?

With Lift Coefficient Roll Control (C_l), Lift Coefficient Slope Roll Control (C_lα) & Flap Effectiveness Parameter (τ) we can find Deflection Angle given Lift Coefficient using the formula - Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter).

Can the Deflection Angle given Lift Coefficient be negative?

Yes, the Deflection Angle given Lift Coefficient, measured in Angle can be negative.

Which unit is used to measure Deflection Angle given Lift Coefficient?

Deflection Angle given Lift Coefficient is usually measured using the Radian[rad] for Angle. Degree[rad], Minute[rad], Second[rad] are the few other units in which Deflection Angle given Lift Coefficient can be measured.

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Deflection Angle given Lift Coefficient Formula

Deflection Angle given Lift Coefficient Example

Deflection Angle given Lift Coefficient Solution

Deflection Angle given Lift Coefficient Formula Elements

Other formulas in Lateral Control category

How to Evaluate Deflection Angle given Lift Coefficient?

FAQs on Deflection Angle given Lift Coefficient

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