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Calculate the Lift and Drag force on a NACA 0012 airfoil with std. roughness at Re=6million operating at 4 degrees angle of attack in a relative wind of 16m/s, and a length of 35 meters in standard atmosphere

Question

Calculate the Lift and Drag force on a NACA 0012 airfoil

With the following parameters:

  • Standard roughness
  • Reynolds number (Re) = 6 million
  • Angle of attack = 4 degrees
  • Relative wind speed = 16 m/s
  • Airfoil length = 35 meters
  • Standard atmosphere conditions

Please perform the necessary calculations.

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Solution

Para calcular las fuerzas de sustentación y arrastre en un perfil alar NACA 0012 con rugosidad estándar a un número de Reynolds de 6 millones, operando a un ángulo de ataque de 4 grados en un viento relativo de 16 m/s y una longitud de 35 metros en una atmósfera estándar, seguiremos los siguientes pasos:

  1. Determinar las propiedades del aire en la atmósfera estándar:

    • Densidad del aire (ρ\rho): Aproximadamente 1.225 kg/m³ a nivel del mar.
    • Viscosidad dinámica del aire (μ\mu): Aproximadamente 1.7894×1051.7894 \times 10^{-5} kg/(m·s).
  2. Calcular el área de referencia (A):

    • Para un perfil alar, el área de referencia es el producto de la envergadura (b) y la cuerda (c). En este caso, la longitud dada es la envergadura.
    • Supongamos que la cuerda (c) es 1 metro (esto es una suposición, ya que no se proporciona en el problema).

    A=b×c=35m×1m=35m2 A = b \times c = 35 \, \text{m} \times 1 \, \text{m} = 35 \, \text{m}^2

  3. Calcular el coeficiente de sustentación (CLC_L) y el coeficiente de arrastre (CDC_D):

    • Para un perfil NACA 0012 a un ángulo de ataque de 4 grados, los valores típicos de CLC_L y CDC_D se pueden obtener de tablas o gráficos aerodinámicos. Aproximadamente:
      • CL0.6C_L \approx 0.6
      • CD0.02C_D \approx 0.02
  4. Calcular la velocidad dinámica (qq):

    q=12ρV2=12×1.225kg/m3×(16m/s)2=156.8N/m2 q = \frac{1}{2} \rho V^2 = \frac{1}{2} \times 1.225 \, \text{kg/m}^3 \times (16 \, \text{m/s})^2 = 156.8 \, \text{N/m}^2

  5. Calcular la fuerza de sustentación (L):

    L=CL×q×A=0.6×156.8N/m2×35m2=3292.8N L = C_L \times q \times A = 0.6 \times 156.8 \, \text{N/m}^2 \times 35 \, \text{m}^2 = 3292.8 \, \text{N}

  6. Calcular la fuerza de arrastre (D):

    D=CD×q×A=0.02×156.8N/m2×35m2=109.76N D = C_D \times q \times A = 0.02 \times 156.8 \, \text{N/m}^2 \times 35 \, \text{m}^2 = 109.76 \, \text{N}

Por lo tanto, las fuerzas de sustentación y arrastre en el perfil alar NACA 0012 son aproximadamente:

  • Fuerza de sustentación (L): 3292.8 N
  • Fuerza de arrastre (D): 109.76 N

This problem has been solved

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