Aileron Deflection given Aileron Lift Coefficient 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 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 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%

✖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]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Lateral Control Formulas PDF PDF Image

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 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
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 00.007 seconds)

You are here -

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

Credits

Created by LOKESH

Sri Ramakrishna Engineering College (SREC), COIMBATORE

LOKESH has created this Calculator and 25+ more calculators!

Verified by Harsh Raj

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

Harsh Raj has verified this Calculator and 100+ more calculators!

< 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)

Aileron Deflection given Aileron Lift Coefficient Formula

LaTeX Go

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.

What is Aileron Deflection?

Aileron deflection refers to the movement of an aircraft's ailerons, which are hinged control surfaces located on the trailing edge of each wing, up or down from their neutral position. This movement is typically controlled by the pilot via the control yoke or stick. Aileron deflection alters the aerodynamic forces on the wings, producing a rolling motion about the aircraft's longitudinal axis.

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 a measure of the relationship between the deflection of an aileron and its corresponding lift coefficient, taking into account the derivative of wing lift coefficient, flap effectiveness, wing area, wingspan, and chord length. 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 a measure of the relationship between the deflection of an aileron and its corresponding lift coefficient, taking into account the derivative of wing lift coefficient, flap effectiveness, wing area, wingspan, and chord length 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 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 Aileron Deflection given Aileron Lift Coefficient?

The Aileron Deflection given Aileron Lift Coefficient formula is a measure of the relationship between the deflection of an aileron and its corresponding lift coefficient, taking into account the derivative of wing lift coefficient, flap effectiveness, wing area, wingspan, and chord length 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

Home

FREE PDFs

🔍 Search