Roll Control Power Calculator

✖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 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 is the distance between the trailing edge and the point where the chord intersects the leading edge.ⓘ Chord [c]			+10% -10%
✖Initial Length is a length between wing center to aileron start point.ⓘ Initial Length [y₁]			+10% -10%
✖Final Length is a length between center of wing to the aileron end point.ⓘ Final Length [y₂]			+10% -10%

✖Roll Control Power is a function of the roll inertia of an airplane and the roll-control power of the ailerons.ⓘ Roll Control Power [Cl_δα]

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Roll Control Power Solution

STEP 0: Pre-Calculation Summary

Formula Used

Roll Control Power = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length)
Cl_δα = (2*C_lαw*τ)/(S*b)*int(c*x,x,y₁,y₂)
This formula uses 1 Functions, 8 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

Roll Control Power - (Measured in Radian) - Roll Control Power is a function of the roll inertia of an airplane and the roll-control power of the ailerons.
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.
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 is the distance between the trailing edge and the point where the chord intersects the leading edge.
Initial Length - (Measured in Meter) - Initial Length is a length between wing center to aileron start point.
Final Length - (Measured in Meter) - Final Length 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
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

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

Evaluating ... ...

Cl_δα = 0.0132903132352941

STEP 3: Convert Result to Output's Unit

0.0132903132352941 Radian --> No Conversion Required

FINAL ANSWER

0.0132903132352941 ≈ 0.01329 Radian <-- Roll Control Power

(Calculation completed in 00.004 seconds)

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Created by LOKESH

Sri Ramakrishna Engineering College (SREC), COIMBATORE

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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

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< Lateral Control Calculators

Aileron Deflection given Aileron Lift Coefficient

LaTeX 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)

Roll Control Power

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

Aileron Section lift Coefficient given Aileron Deflection

LaTeX 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

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

Roll Control Power Formula

LaTeX Go

What is Roll control power of aileron?

The roll control power of the ailerons is a function of both the configuration of the airplane and of airspeed. The shape, size, deflection and spanwise position of the ailerons all affect the amount of rolling moment the ailerons can generate.

How to Calculate Roll Control Power?

Roll Control Power calculator 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 calculate 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 calculate Roll Control Power using this online calculator? To use this online calculator 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. Here is how the Roll Control Power calculation can be explained with given input values -> 0.01329 = (2*0.23*0.66)/(17*200)*int(2.1*x,x,1.5,12).

FAQ

What is 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 and is represented as Cl_δα = (2*C_lαw*τ)/(S*b)*int(c*x,x,y₁,y₂) or Roll Control Power = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter)/(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 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 is the distance between the trailing edge and the point where the chord intersects the leading edge, Initial Length is a length between wing center to aileron start point & Final Length is a length between center of wing to the aileron end point.

How to calculate 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 is calculated using Roll Control Power = (2*Derivative of Wing Lift Coefficient*Flap Effectiveness Parameter)/(Wing Area*Wingspan)*int(Chord*x,x,Initial Length,Final Length). To calculate Roll Control Power, you need Derivative of Wing Lift Coefficient (C_lαw), Flap Effectiveness Parameter (τ), 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, 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.

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