Deflection Angle given Lift Coefficient Calculator

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Static Stability and Control

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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.ⓘ Lift Coefficient Roll Control [C_l]			+10% -10%
✖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.ⓘ Lift Coefficient Slope Roll Control [C_lα]			+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 Angle given Lift Coefficient [δ_a]

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Formula

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Deflection Angle given Lift Coefficient

Formula

`"δ"_{"a"} = "C"_{"l"}/("C"_{"lα"}*"τ")`

Example

`"5.530303rad"="0.073"/("0.02"*"0.66")`

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Deflection Angle given Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter)
δ_a = C_l/(C_lα*τ)
This formula uses 4 Variables

Variables Used

Deflection of Aileron - (Measured in Radian) - The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position.
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.
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.
Flap Effectiveness Parameter - The flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient Roll Control: 0.073 --> No Conversion Required
Lift Coefficient Slope Roll Control: 0.02 --> No Conversion Required
Flap Effectiveness Parameter: 0.66 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

δ_a = C_l/(C_lα*τ) --> 0.073/(0.02*0.66)

Evaluating ... ...

δ_a = 5.53030303030303

STEP 3: Convert Result to Output's Unit

5.53030303030303 Radian --> No Conversion Required

FINAL ANSWER

5.53030303030303 ≈ 5.530303 Radian <-- Deflection of Aileron

(Calculation completed in 00.007 seconds)

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< 10+ Lateral Control Calculators

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

Deflection Angle given Lift Coefficient Formula

Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter)
δ_a = C_l/(C_lα*τ)

what is Deflection Angle ?

The deflection angle of a control surface, such as an aileron, elevator, or rudder, refers to the angle at which that surface is deflected from its neutral or zero position. This angle is measured relative to the surface's neutral position, which is typically where the control surface lies when there is no input from the pilot.

How to Calculate Deflection Angle given Lift Coefficient?

Deflection Angle given Lift Coefficient calculator uses Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter) to calculate 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 calculate Deflection Angle given Lift Coefficient using this online calculator? To use this online calculator 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. Here is how the Deflection Angle given Lift Coefficient calculation can be explained with given input values -> 5.530303 = 0.073/(0.02*0.66).

FAQ

What is Deflection Angle given Lift Coefficient?

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 and is represented as δ_a = C_l/(C_lα*τ) or Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter). 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, 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 & The flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.

How to calculate Deflection Angle given Lift Coefficient?

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 is calculated using Deflection of Aileron = Lift Coefficient Roll Control/(Lift Coefficient Slope Roll Control*Flap Effectiveness Parameter). To calculate Deflection Angle given Lift Coefficient, you need Lift Coefficient Roll Control (C_l), Lift Coefficient Slope Roll Control (C_lα) & Flap Effectiveness Parameter (τ). With our tool, you need to enter the respective value for Lift Coefficient Roll Control, Lift Coefficient Slope Roll Control & Flap Effectiveness Parameter and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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