How to Get appropriate flags for a Cambered Airfoil?

[iabhishek44]

I've been trying to simulate a 2D, cambered airfoil by creating a new shape function. I used the mean camber line equation in an attempt to get the shape for the airfoil. However, unlike a symmetric airfoil which gets captured successfully, the camber equation is giving me mixed results. I am attaching my code for the shape function.

bool airfoil(const uint x, const uint y, const uint z, const float3& p, const float c, const float t, const float p_c, const float m_c)
{

const float3 l = float3(x, y, z) - p;
const float x_l = l.x/c ;
const float y_l = l.y/c ;
const float c_0 = 0.2969f * sqrt(y_l);
const float c_1 = -0.1260f * (y_l);
const float c_2 = -0.3516f * sq(y_l);
const float c_3 = 0.2843f * cb(y_l);
const float c_4 = -0.1036f * pow(y_l, 4.0f);
const float y_t = 5.0f * t * (c_0 + c_1 + c_2 + c_3 + c_4);

float y_ci = 0.0f;
float dyc_dx = 0.0f;

if (0.0f <= y_l && y_l <= p_c)
{
    y_ci = (m_c/sq(p_c))*((2.0f*p_c*y_l)-(sq(y_l)));
    dyc_dx = ((2.0f * m_c)/sq(p_c))*(p_c-y_l);
}

else if(p_c <= y_l && y_l <= 1.0f)
{
    y_ci = (m_c/sq(1-p_c)) * ((2*p_c*y_l) - (sq(y_l)));
    dyc_dx = ((2.0f*m_c)/(sq(1-p_c)))*(p_c-y_l);
}
// Check if the point (x, y) is within the thickness limits

const float theta1 = atan(dyc_dx);
const float y_coordu = y_ci + ((y_t)*cos(theta1));
const float y_coordl = y_ci - ((y_t)*cos(theta1));
const float x_coordu = y_l - ((y_t)*sin(theta1));
const float x_coordl = y_l + ((y_t)*sin(theta1));

const bool l_check = (fabs(l.x) >= x_coordl || fabs(l.y) >= y_coordl);
const bool u_check = (fabs(l.x) <= x_coordu || fabs(l.y) <= y_coordu);

return(l_check && u_check);
}

I tried to model it after the numerous shape functions available on FluidX3D's shapes.cpp package, but I guess I am messing up some portion of the code.

Thank you for the help!