Aerofoil Thickness for 4 Digit Series Calculator

Aerofoil Thickness Formula:

\[ y_t = \frac{t \times (0.2969 \times x^{0.5} - 0.1260 \times x - 0.3516 \times x^2 + 0.2843 \times x^3 - 0.1015 \times x^4)}{0.2} \]

Half Thickness (y_t):

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1. What is the Aerofoil Thickness Formula?

The Aerofoil Thickness Formula for 4-digit NACA series calculates the half-thickness of an airfoil at any position along the chord. This formula is essential for aerodynamic design and analysis of airfoil profiles.

2. How Does the Calculator Work?

The calculator uses the aerofoil thickness formula:

\[ y_t = \frac{t \times (0.2969 \times x^{0.5} - 0.1260 \times x - 0.3516 \times x^2 + 0.2843 \times x^3 - 0.1015 \times x^4)}{0.2} \]

Where:

\( y_t \) — Half thickness of the airfoil (m)
\( t \) — Maximum thickness (fraction of chord length) (m)
\( x \) — Position along the chord (0 to 1)

Explanation: The formula provides the symmetrical thickness distribution for NACA 4-digit series airfoils, where the maximum thickness occurs at 30% of the chord from the leading edge.

3. Importance of Aerofoil Thickness Calculation

Details: Accurate thickness calculation is crucial for aerodynamic performance analysis, structural design, and understanding the flow characteristics around airfoils. It affects lift, drag, and moment coefficients.

4. Using the Calculator

Tips: Enter maximum thickness in meters and position along the chord (0 to 1, where 0 is leading edge and 1 is trailing edge). Both values must be valid (thickness > 0, position between 0-1).

5. Frequently Asked Questions (FAQ)

Q1: What are NACA 4-digit series airfoils?
A: NACA 4-digit series are standardized airfoil shapes developed by NASA, where the first digit indicates maximum camber, second digit shows camber position, and last two digits specify maximum thickness.

Q2: Where is maximum thickness typically located?
A: For NACA 4-digit series airfoils, maximum thickness is typically located at 30% of the chord length from the leading edge.

Q3: What is the significance of half thickness?
A: Half thickness represents the distance from the mean camber line to the airfoil surface, used to construct the complete airfoil shape.

Q4: Can this formula be used for cambered airfoils?
A: This specific formula calculates thickness distribution only. For cambered airfoils, the mean camber line must be calculated separately and combined with the thickness distribution.

Q5: What are typical applications of this calculation?
A: Used in aircraft wing design, turbine blade design, propeller design, and any application requiring optimized aerodynamic surfaces.