Aileron Deflection Given Aileron Lift Coefficient Calculator

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Static Stability and Control

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Aircraft Performance

Introduction and Governing Equations

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Lateral Control

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✖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.ⓘ Derivative of Wing Lift Coefficient [C_lαw]			+10% -10%
✖The flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.ⓘ Flap Effectiveness Parameter [τ]			+10% -10%
✖The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position.ⓘ Deflection of Aileron [δ_a]			+10% -10%
✖The Wing area, S, is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips.ⓘ Wing Area [S]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖The chord the distance between the trailing edge and the point where the chord intersects the leading edge.ⓘ Chord [c]			+10% -10%
✖Initial length roll control is a length between wing center to aileron start point.ⓘ Initial Length [y₁]			+10% -10%
✖Final length roll control is a length between center of wing to the aileron end point.ⓘ Final Length [y₂]			+10% -10%

✖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.ⓘ Aileron Deflection Given Aileron Lift Coefficient [C_l]

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Formula

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Aileron Deflection Given Aileron Lift Coefficient

Formula

`"C"_{"l"} = (2*"C"_{"lαw"}*"τ"*"δ"_{"a"})/("S"*"b")*int("c"*x,x,"y"_{"1"},"y"_{"2"})`

Example

`"0.073097"=(2*"0.23"*"0.66"*"5.5rad")/("17m²"*"200m")*int("2.1m"*x,x,"1.5m","12m")`

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Aileron Deflection Given Aileron Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)
C_l = (2*C_lαw*τ*δ_a)/(S*b)*int(c*x,x,y₁,y₂)
This formula uses 1 Functions, 9 Variables

Functions Used

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., int(expr, arg, from, to)

Variables Used

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.
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.
Flap Effectiveness Parameter - The flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.
Deflection of Aileron - (Measured in Radian) - The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position.
Wing Area - (Measured in Square Meter) - The Wing area, S, is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Chord - (Measured in Meter) - The chord the distance between the trailing edge and the point where the chord intersects the leading edge.
Initial Length - (Measured in Meter) - Initial length roll control is a length between wing center to aileron start point.
Final Length - (Measured in Meter) - Final length roll control is a length between center of wing to the aileron end point.

STEP 1: Convert Input(s) to Base Unit

Derivative of Wing Lift Coefficient: 0.23 --> No Conversion Required
Flap Effectiveness Parameter: 0.66 --> No Conversion Required
Deflection of Aileron: 5.5 Radian --> 5.5 Radian No Conversion Required
Wing Area: 17 Square Meter --> 17 Square Meter No Conversion Required
Wingspan: 200 Meter --> 200 Meter No Conversion Required
Chord: 2.1 Meter --> 2.1 Meter No Conversion Required
Initial Length: 1.5 Meter --> 1.5 Meter No Conversion Required
Final Length: 12 Meter --> 12 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_l = (2*C_lαw*τ*δ_a)/(S*b)*int(c*x,x,y₁,y₂) --> (2*0.23*0.66*5.5)/(17*200)*int(2.1*x,x,1.5,12)

Evaluating ... ...

C_l = 0.0730967227941177

STEP 3: Convert Result to Output's Unit

0.0730967227941177 --> No Conversion Required

FINAL ANSWER

0.0730967227941177 ≈ 0.073097 <-- Lift Coefficient Roll Control

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Lateral Control » Aileron Deflection Given Aileron Lift Coefficient

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Aileron Deflection Given Aileron Lift Coefficient

Go 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)

Lift Coefficient with respect to Roll Rate

Go Lift Coefficient Respect to Roll Rate = -((2*Roll Rate)/(Wing Reference Area*Wingspan*Reference Velocity Across X Axis))*int(Lift Curve Slope*Chord*x^2,x,0,Wingspan/2)

Roll Control Power

Go Roll Control Power = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length)

Lift given Roll Rate

Go Lift Respect to Roll Rate = -2*int(Lift Curve Slope*((Roll Rate*x)/Reference Velocity Across X Axis)*Pitch Rate*Chord*x,x,0,Wingspan/2)

Roll Damping Coefficient

Go Roll Damping Coefficient = -(4*Derivative of Wing Lift Coefficient)/(Wing Area*Wingspan^2)*int(Chord*x^2,x,0,Wingspan/2)

Aileron Section lift Coefficient given Aileron Deflection

Go 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

Aileron Control Effectiveness given Aileron Deflection

Go Flap Effectiveness Parameter = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Deflection of Aileron)

Deflection Angle given Lift Coefficient

Go Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter)

Lift Coefficient Slope Roll Control

Go Lift Coefficient Slope Roll Control = Lift Coefficient Roll Control/(Deflection of Aileron*Flap Effectiveness Parameter)

Aileron Section Lift Coefficient given Control Effectiveness

Go Lift Coefficient Roll Control = Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter*Deflection of Aileron

Aileron Deflection Given Aileron Lift Coefficient Formula

What is Aileron Deflection given Aileron Lift Coefficient ?

The Aileron Deflection given Aileron Lift Coefficient is the lift coefficient of an aileron given its deflection angle depends on its geometry, airfoil characteristics, and flow conditions. It's typically determined experimentally or computationally by analyzing lift forces at various deflection angles.

How to Calculate Aileron Deflection Given Aileron Lift Coefficient?

Aileron Deflection Given Aileron Lift Coefficient calculator 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 calculate the Lift Coefficient Roll Control, The Aileron Deflection given Aileron Lift Coefficient formula is defined as Aileron Lift Coefficient. Lift Coefficient Roll Control is denoted by C_l symbol.

How to calculate Aileron Deflection Given Aileron Lift Coefficient using this online calculator? To use this online calculator 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. Here is how the Aileron Deflection Given Aileron Lift Coefficient calculation can be explained with given input values -> 0.085989 = (2*0.23*0.66*5.5)/(17*200)*int(2.1*x,x,1.5,12).

FAQ

What is Aileron Deflection Given Aileron Lift Coefficient?

The Aileron Deflection given Aileron Lift Coefficient formula is defined as Aileron Lift Coefficient and is represented as C_l = (2*C_lαw*τ*δ_a)/(S*b)*int(c*x,x,y₁,y₂) or 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). 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, The flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance, The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position, The Wing area, S, is the projected area of the planform and is bounded by the leading and trailing edges and the wing tips, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, The chord the distance between the trailing edge and the point where the chord intersects the leading edge, Initial length roll control is a length between wing center to aileron start point & Final length roll control is a length between center of wing to the aileron end point.

How to calculate Aileron Deflection Given Aileron Lift Coefficient?

The Aileron Deflection given Aileron Lift Coefficient formula is defined as Aileron Lift Coefficient is calculated using 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 calculate Aileron Deflection Given Aileron Lift Coefficient, you need 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). With our tool, you need to enter the respective value for Derivative of Wing Lift Coefficient, Flap Effectiveness Parameter, Deflection of Aileron, Wing Area, Wingspan, Chord, Initial Length & Final Length and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Lift Coefficient Roll Control?

In this formula, Lift Coefficient Roll Control uses Derivative of Wing Lift Coefficient, Flap Effectiveness Parameter, Deflection of Aileron, Wing Area, Wingspan, Chord, Initial Length & Final Length. We can use 2 other way(s) to calculate the same, which is/are as follows -

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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