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Aileron Deflection given Aileron Lift Coefficient Formula

GoAileron Section lift Coefficient given Aileron Deflection Formula

GoAileron Section Lift Coefficient given Control Effectiveness Formula

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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. Check FAQs

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)

C_l - Lift Coefficient Roll Control?C_lαw - Derivative of Wing Lift Coefficient?τ - Flap Effectiveness Parameter?δ_a - Deflection of Aileron?S - Wing Area?b - Wingspan?c - Chord?y₁ - Initial Length?y₂ - Final Length?

Aileron Deflection given Aileron Lift Coefficient Example

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

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

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

0.0731 = \frac{2 \cdot 0.23 \cdot 0.66 \cdot 5.5}{17 \cdot 200} \cdot \int (2.1 \cdot x, x, 1.5, 12)

0.0731 = \frac{2 \cdot 0.23 \cdot 0.66 \cdot 5.5rad}{17m² \cdot 200m} \cdot \int (2.1m \cdot x, x, 1.5m, 12m)

0.0731 = \frac{2 \cdot 0.23 \cdot 0.66 \cdot 5.5}{17 \cdot 200} \cdot \int (2.1 \cdot x, x, 1.5, 12)

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Aileron Deflection given Aileron Lift Coefficient Solution

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

FIRST Step Consider the formula

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)

Next Step Substitute values of Variables

∴

C l = \frac{2 \cdot 0.23 \cdot 0.66 \cdot 5.5rad}{17m² \cdot 200m} \cdot \int (2.1m \cdot x, x, 1.5m, 12m)

Next Step Prepare to Evaluate

∴

C l = \frac{2 \cdot 0.23 \cdot 0.66 \cdot 5.5}{17 \cdot 200} \cdot \int (2.1 \cdot x, x, 1.5, 12)

Next Step Evaluate

∴

C l = 0.0730967227941177

LAST Step Rounding Answer

∴

C l = 0.0731

Aileron Deflection given Aileron Lift Coefficient Formula Elements

Variables

Functions

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

Derivative of Wing Lift Coefficient

Derivative of Wing Lift Coefficient is the lift curve slope, which is a measure of how much lift changes when the angle of attack of an aircraft changes.

Symbol: C_lαw

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Derivative of Wing Lift Coefficient

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

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

Wing Area

The Wing Area, S, is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips.

Symbol: S

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Wing 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

Chord

The Chord is the distance between the trailing edge and the point where the chord intersects the leading edge.

Symbol: c

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Chord

Initial Length

Initial Length is a length between wing center to aileron start point.

Symbol: y₁

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Initial Length

Final Length

Final Length is a length between center of wing to the aileron end point.

Symbol: y₂

Measurement: LengthUnit: m

Note: Value should be greater than 0.

Formulas to find Final Length

int

The definite integral can be used to calculate net signed area, which is the area above the x -axis minus the area below the x -axis.

Syntax: int(expr, arg, from, to)

Other Formulas to find Lift Coefficient Roll Control

Go Aileron Section lift Coefficient given Aileron Deflection

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

Go Aileron Section Lift Coefficient given Control Effectiveness

C l = C lα \cdot τ \cdot δ a

Other formulas in Lateral Control category

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 Aileron Deflection given Aileron Lift Coefficient?

Aileron Deflection given Aileron Lift Coefficient evaluator uses Lift Coefficient Roll Control = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter*Deflection of Aileron)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length) to evaluate the Lift Coefficient Roll Control, The Aileron Deflection given Aileron Lift Coefficient formula is a measure of the relationship between the deflection of an aileron and its corresponding lift coefficient, taking into account the derivative of wing lift coefficient, flap effectiveness, wing area, wingspan, and chord length. Lift Coefficient Roll Control is denoted by C_l symbol.

How to evaluate Aileron Deflection given Aileron Lift Coefficient using this online evaluator? To use this online evaluator for Aileron Deflection given Aileron Lift Coefficient, enter Derivative of Wing Lift Coefficient (C_lαw), Flap Effectiveness Parameter (τ), Deflection of Aileron (δ_a), Wing Area (S), Wingspan (b), Chord (c), Initial Length (y₁) & Final Length (y₂) and hit the calculate button.

FAQs on Aileron Deflection given Aileron Lift Coefficient

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

The formula of Aileron Deflection given Aileron Lift Coefficient is expressed as Lift Coefficient Roll Control = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter*Deflection of Aileron)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length). Here is an example- 0.085989 = (2*0.23*0.66*5.5)/(17*200)*int(2.1*x,x,1.5,12).

How to calculate Aileron Deflection given Aileron Lift Coefficient?

With Derivative of Wing Lift Coefficient (C_lαw), Flap Effectiveness Parameter (τ), Deflection of Aileron (δ_a), Wing Area (S), Wingspan (b), Chord (c), Initial Length (y₁) & Final Length (y₂) we can find Aileron Deflection given Aileron Lift Coefficient using the formula - Lift Coefficient Roll Control = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter*Deflection of Aileron)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length). This formula also uses Definite Integral (int) function(s).

What are the other ways to Calculate Lift Coefficient Roll Control?

Here are the different ways to Calculate Lift Coefficient Roll Control-

Lift Coefficient Roll Control=Lift Coefficient Slope Roll Control*(Rate of change of Angle of Attack/Rate of change of Deflection of Aileron)*Deflection of Aileron
Lift Coefficient Roll Control=Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter*Deflection of Aileron

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Aileron Deflection given Aileron Lift Coefficient Formula

​GoAileron Section lift Coefficient given Aileron Deflection Formula

​GoAileron Section Lift Coefficient given Control Effectiveness Formula

Aileron Deflection given Aileron Lift Coefficient Example

Aileron Deflection given Aileron Lift Coefficient Solution

Aileron Deflection given Aileron Lift Coefficient Formula Elements

Other Formulas to find Lift Coefficient Roll Control

Other formulas in Lateral Control category

How to Evaluate Aileron Deflection given Aileron Lift Coefficient?

FAQs on Aileron Deflection given Aileron Lift Coefficient

Variable Name

GoAileron Section lift Coefficient given Aileron Deflection Formula

GoAileron Section Lift Coefficient given Control Effectiveness Formula