Aerofoil Thickness for 4 Digit Series Calculator

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✖Maximum Thickness is the fraction of the chord length.ⓘ Maximum Thickness [t]			+10% -10%
✖Position Along The chord is the distance between the trailing edge and the point where the chord intersects the leading edge.ⓘ Position Along the chord [x]			+10% -10%

✖The Half Thickness of the airfoil is the thickness at a distance of x from the leading edge.ⓘ Aerofoil Thickness for 4 Digit Series [y_t]

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Formula

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Aerofoil Thickness for 4 Digit Series

Formula

`"y"_{"t"} = ("t"*(0.2969*"x"^0.5-0.1260*"x"-0.3516*"x"^2+0.2843*"x"^3-0.1015*"x"^4))/0.2`

Example

`"0.066175m"=("0.15m"*(0.2969*("0.5")^0.5-0.1260*"0.5"-0.3516*("0.5")^2+0.2843*("0.5")^3-0.1015*("0.5")^4))/0.2`

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Aerofoil Thickness for 4 Digit Series Solution

STEP 0: Pre-Calculation Summary

Formula Used

Half Thickness = (Maximum Thickness*(0.2969*Position Along the chord^0.5-0.1260*Position Along the chord-0.3516*Position Along the chord^2+0.2843*Position Along the chord^3-0.1015*Position Along the chord^4))/0.2
y_t = (t*(0.2969*x^0.5-0.1260*x-0.3516*x^2+0.2843*x^3-0.1015*x^4))/0.2
This formula uses 3 Variables

Variables Used

Half Thickness - (Measured in Meter) - The Half Thickness of the airfoil is the thickness at a distance of x from the leading edge.
Maximum Thickness - (Measured in Meter) - Maximum Thickness is the fraction of the chord length.
Position Along the chord - Position Along The chord is the distance between the trailing edge and the point where the chord intersects the leading edge.

STEP 1: Convert Input(s) to Base Unit

Maximum Thickness: 0.15 Meter --> 0.15 Meter No Conversion Required
Position Along the chord: 0.5 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

y_t = (t*(0.2969*x^0.5-0.1260*x-0.3516*x^2+0.2843*x^3-0.1015*x^4))/0.2 --> (0.15*(0.2969*0.5^0.5-0.1260*0.5-0.3516*0.5^2+0.2843*0.5^3-0.1015*0.5^4))/0.2

Evaluating ... ...

y_t = 0.0661753150007145

STEP 3: Convert Result to Output's Unit

0.0661753150007145 Meter --> No Conversion Required

FINAL ANSWER

0.0661753150007145 ≈ 0.066175 Meter <-- Half Thickness

(Calculation completed in 00.004 seconds)

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Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai

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< 13 Aerodynamic Design Calculators

Aerofoil Thickness for 4 Digit Series

Go Half Thickness = (Maximum Thickness*(0.2969*Position Along the chord^0.5-0.1260*Position Along the chord-0.3516*Position Along the chord^2+0.2843*Position Along the chord^3-0.1015*Position Along the chord^4))/0.2

Thrust-to-Weight Ratio given Minimum Coefficient of Drag

Go Thrust-to-Weight Ratio = (Minimum Drag Coefficient/Wing Loading+Lift Induced Drag Constant*(Load Factor/Dynamic Pressure)^2*Wing Loading)*Dynamic Pressure

Span given Induced Drag

Go Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure)

Form Factor given Flat Plate Area

Go Form Factor Drag = (Flat Plate Area)/(Skin Friction Coefficient*Aircraft Wetted Area)

Skin Friction Coefficient given Flat Plate Area

Go Skin Friction Coefficient = Flat Plate Area/(Form Factor Drag*Aircraft Wetted Area)

Wetted Area given Flat Plate Area

Go Aircraft Wetted Area = Flat Plate Area/(Form Factor Drag*Skin Friction Coefficient)

Equivalent Parasite Drag Area

Go Flat Plate Area = Form Factor Drag*Skin Friction Coefficient*Aircraft Wetted Area

Span given Aspect Ratio

Go Lateral Plane Span = sqrt(Aspect Ratio in Lateral Plane*Aircraft Wetted Area)

Gross weight given drag

Go Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient)

Wetted Area given Aspect Ratio

Go Aircraft Wetted Area = Lateral Plane Span^2/Aspect Ratio in Lateral Plane

Aspect Ratio of Wing

Go Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area

Taper Ratio of Airfoil

Go Taper Ratio = Tip Chord Length/Root Chord Length

Tip Speed Ratio with Blade Number

Go Tip Speed Ratio = (4*pi)/Number of Blades

Aerofoil Thickness for 4 Digit Series Formula

Does thickness of airfoil affect lift?

Increasing the thickness will increase the lift. Increasing the area will increase the lift. Increasing the altitude will decrease the lift.

How to Calculate Aerofoil Thickness for 4 Digit Series?

Aerofoil Thickness for 4 Digit Series calculator uses Half Thickness = (Maximum Thickness*(0.2969*Position Along the chord^0.5-0.1260*Position Along the chord-0.3516*Position Along the chord^2+0.2843*Position Along the chord^3-0.1015*Position Along the chord^4))/0.2 to calculate the Half Thickness, The Aerofoil Thickness for 4 Digit Series refers to the maximum thickness of the airfoil, expressed as a percentage of the chord length. This formula calculates the thickness distribution of the airfoil at any point along the chord length x, where 0≤x≤1. Half Thickness is denoted by y_t symbol.

How to calculate Aerofoil Thickness for 4 Digit Series using this online calculator? To use this online calculator for Aerofoil Thickness for 4 Digit Series, enter Maximum Thickness (t) & Position Along the chord (x) and hit the calculate button. Here is how the Aerofoil Thickness for 4 Digit Series calculation can be explained with given input values -> 0.066175 = (0.15*(0.2969*0.5^0.5-0.1260*0.5-0.3516*0.5^2+0.2843*0.5^3-0.1015*0.5^4))/0.2.

FAQ

What is Aerofoil Thickness for 4 Digit Series?

The Aerofoil Thickness for 4 Digit Series refers to the maximum thickness of the airfoil, expressed as a percentage of the chord length. This formula calculates the thickness distribution of the airfoil at any point along the chord length x, where 0≤x≤1 and is represented as y_t = (t*(0.2969*x^0.5-0.1260*x-0.3516*x^2+0.2843*x^3-0.1015*x^4))/0.2 or Half Thickness = (Maximum Thickness*(0.2969*Position Along the chord^0.5-0.1260*Position Along the chord-0.3516*Position Along the chord^2+0.2843*Position Along the chord^3-0.1015*Position Along the chord^4))/0.2. Maximum Thickness is the fraction of the chord length & Position Along The chord is the distance between the trailing edge and the point where the chord intersects the leading edge.

How to calculate Aerofoil Thickness for 4 Digit Series?

The Aerofoil Thickness for 4 Digit Series refers to the maximum thickness of the airfoil, expressed as a percentage of the chord length. This formula calculates the thickness distribution of the airfoil at any point along the chord length x, where 0≤x≤1 is calculated using Half Thickness = (Maximum Thickness*(0.2969*Position Along the chord^0.5-0.1260*Position Along the chord-0.3516*Position Along the chord^2+0.2843*Position Along the chord^3-0.1015*Position Along the chord^4))/0.2. To calculate Aerofoil Thickness for 4 Digit Series, you need Maximum Thickness (t) & Position Along the chord (x). With our tool, you need to enter the respective value for Maximum Thickness & Position Along the chord 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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