Lift Coefficient Slope Roll Control 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%
✖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 flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.ⓘ Flap Effectiveness Parameter [τ]			+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]

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Formula

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Lift Coefficient Slope Roll Control

Formula

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

Example

`"0.02011"="0.073"/("5.5rad"*"0.66")`

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Lift Coefficient Slope Roll Control Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
Deflection of Aileron - (Measured in Radian) - The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position.
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
Deflection of Aileron: 5.5 Radian --> 5.5 Radian No Conversion Required
Flap Effectiveness Parameter: 0.66 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_lα = C_l/(δ_a*τ) --> 0.073/(5.5*0.66)

Evaluating ... ...

C_lα = 0.0201101928374656

STEP 3: Convert Result to Output's Unit

0.0201101928374656 --> No Conversion Required

FINAL ANSWER

0.0201101928374656 ≈ 0.02011 <-- Lift Coefficient Slope Roll Control

(Calculation completed in 00.004 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

Lift Coefficient Slope Roll Control Formula

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

what is Lift Coefficient Slope ?

The lift coefficient slope represents the rate of change of the lift coefficient with respect to the angle of attack, it quantifies how much the lift coefficient changes as the angle of attack varies.

How to Calculate Lift Coefficient Slope Roll Control?

Lift Coefficient Slope Roll Control calculator uses Lift Coefficient Slope Roll Control = Lift Coefficient Roll Control/(Deflection of Aileron*Flap Effectiveness Parameter) to calculate the Lift Coefficient Slope Roll Control, The Lift Coefficient Slope Roll Control formula calculates the how the lift of an airfoil or wing varies with changes in the angle of attack, with given lift coefficient. Lift Coefficient Slope Roll Control is denoted by C_lα symbol.

How to calculate Lift Coefficient Slope Roll Control using this online calculator? To use this online calculator for Lift Coefficient Slope Roll Control, enter Lift Coefficient Roll Control (C_l), Deflection of Aileron (δ_a) & Flap Effectiveness Parameter (τ) and hit the calculate button. Here is how the Lift Coefficient Slope Roll Control calculation can be explained with given input values -> 0.02011 = 0.073/(5.5*0.66).

FAQ

What is Lift Coefficient Slope Roll Control?

The Lift Coefficient Slope Roll Control formula calculates the how the lift of an airfoil or wing varies with changes in the angle of attack, with given lift coefficient and is represented as C_lα = C_l/(δ_a*τ) or Lift Coefficient Slope Roll Control = Lift Coefficient Roll Control/(Deflection of Aileron*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, The Deflection of Aileron refers to the angular displacement of the aileron control surface from its neutral position & The flap effectiveness parameter is a measure of how much flaps improve an aircraft's aerodynamic performance.

How to calculate Lift Coefficient Slope Roll Control?

The Lift Coefficient Slope Roll Control formula calculates the how the lift of an airfoil or wing varies with changes in the angle of attack, with given lift coefficient is calculated using Lift Coefficient Slope Roll Control = Lift Coefficient Roll Control/(Deflection of Aileron*Flap Effectiveness Parameter). To calculate Lift Coefficient Slope Roll Control, you need Lift Coefficient Roll Control (C_l), Deflection of Aileron (δ_a) & Flap Effectiveness Parameter (τ). With our tool, you need to enter the respective value for Lift Coefficient Roll Control, Deflection of Aileron & 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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