FormulaDen.com

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

Aileron Control Effectiveness given Aileron Deflection Formula

Fx Copy

LaTeX Copy

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

τ = \frac{C l}{C lα \cdot δ a}

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

Aileron Control Effectiveness given Aileron Deflection Example

With values

With units

Only example

Here is how the Aileron Control Effectiveness given Aileron Deflection equation looks like with Values.

Here is how the Aileron Control Effectiveness given Aileron Deflection equation looks like with Units.

Here is how the Aileron Control Effectiveness given Aileron Deflection equation looks like.

0.6636 = \frac{0.073}{0.02 \cdot 5.5}

0.6636 = \frac{0.073}{0.02 \cdot 5.5rad}

0.6636 = \frac{0.073}{0.02 \cdot 5.5}

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 Aileron Control Effectiveness given Aileron Deflection

Aileron Control Effectiveness given Aileron Deflection Solution

Follow our step by step solution on how to calculate Aileron Control Effectiveness given Aileron Deflection?

FIRST Step Consider the formula

τ = \frac{C l}{C lα \cdot δ a}

Next Step Substitute values of Variables

∴

τ = \frac{0.073}{0.02 \cdot 5.5rad}

Next Step Prepare to Evaluate

∴

τ = \frac{0.073}{0.02 \cdot 5.5}

Next Step Evaluate

∴

τ = 0.663636363636364

LAST Step Rounding Answer

∴

τ = 0.6636

Aileron Control Effectiveness given Aileron Deflection Formula Elements

Variables

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

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

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

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 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)

Go Roll Damping Coefficient

Cl p = - \frac{4 \cdot C lαw}{S \cdot b^{2}} \cdot \int (c \cdot x^{2}, x, 0, \frac{b}{2})

How to Evaluate Aileron Control Effectiveness given Aileron Deflection?

Aileron Control Effectiveness given Aileron Deflection evaluator uses Flap Effectiveness Parameter = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Deflection of Aileron) to evaluate the Flap Effectiveness Parameter, Aileron Control Effectiveness given Aileron Deflection is a measure of the roll control authority of an aircraft, which is the ability of the ailerons to generate a rolling motion, this effectiveness is influenced by the lift coefficient, lift coefficient slope and aileron deflection, it is calculated to determine the responsiveness of the aircraft to control inputs. Flap Effectiveness Parameter is denoted by τ symbol.

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

FAQs on Aileron Control Effectiveness given Aileron Deflection

What is the formula to find Aileron Control Effectiveness given Aileron Deflection?

The formula of Aileron Control Effectiveness given Aileron Deflection is expressed as Flap Effectiveness Parameter = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Deflection of Aileron). Here is an example- 0.663636 = 0.073/(0.02*5.5).

How to calculate Aileron Control Effectiveness given Aileron Deflection?

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

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Aileron Control Effectiveness given Aileron Deflection Formula

Aileron Control Effectiveness given Aileron Deflection Example

Aileron Control Effectiveness given Aileron Deflection Solution

Aileron Control Effectiveness given Aileron Deflection Formula Elements

Other formulas in Lateral Control category

How to Evaluate Aileron Control Effectiveness given Aileron Deflection?

FAQs on Aileron Control Effectiveness given Aileron Deflection

Variable Name