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Roll Control Power Formula

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Roll Control Power is a function of the roll inertia of an airplane and the roll-control power of the ailerons. Check FAQs

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

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

Roll Control Power Example

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Here is how the Roll Control Power equation looks like with Values.

Here is how the Roll Control Power equation looks like with Units.

Here is how the Roll Control Power equation looks like.

0.0133 = \frac{2 \cdot 0.23 \cdot 0.66}{17 \cdot 200} \cdot \int (2.1 \cdot x, x, 1.5, 12)

0.0133rad = \frac{2 \cdot 0.23 \cdot 0.66}{17m² \cdot 200m} \cdot \int (2.1m \cdot x, x, 1.5m, 12m)

0.0133 = \frac{2 \cdot 0.23 \cdot 0.66}{17 \cdot 200} \cdot \int (2.1 \cdot x, x, 1.5, 12)

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Roll Control Power Solution

Follow our step by step solution on how to calculate Roll Control Power?

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

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

Next Step Prepare to Evaluate

∴

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

Next Step Evaluate

∴

Cl δα = 0.0132903132352941rad

LAST Step Rounding Answer

∴

Cl δα = 0.0133rad

Roll Control Power Formula Elements

Variables

Functions

Roll Control Power

Roll Control Power is a function of the roll inertia of an airplane and the roll-control power of the ailerons.

Symbol: Cl_δα

Measurement: AngleUnit: rad

Note: Value should be greater than 0.

Formulas to find Roll Control Power

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

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 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)

How to Evaluate Roll Control Power?

Roll Control Power evaluator uses Roll Control Power = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length) to evaluate the Roll Control Power, Roll Control Power is a measure of the ability of an aircraft's roll control surfaces to generate a rolling moment, calculated as the product of the derivative of wing lift coefficient and flap effectiveness parameter, divided by the product of wing area and wingspan, integrated over the control surface's chord length. Roll Control Power is denoted by Cl_δα symbol.

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

FAQs on Roll Control Power

What is the formula to find Roll Control Power?

The formula of Roll Control Power is expressed as Roll Control Power = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length). Here is an example- 0.01329 = (2*0.23*0.66)/(17*200)*int(2.1*x,x,1.5,12).

How to calculate Roll Control Power?

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

Can the Roll Control Power be negative?

No, the Roll Control Power, measured in Angle cannot be negative.

Which unit is used to measure Roll Control Power?

Roll Control Power is usually measured using the Radian[rad] for Angle. Degree[rad], Minute[rad], Second[rad] are the few other units in which Roll Control Power can be measured.

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Roll Control Power Formula

Roll Control Power Example

Roll Control Power Solution

Roll Control Power Formula Elements

Other formulas in Lateral Control category

How to Evaluate Roll Control Power?

FAQs on Roll Control Power

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