Need help with calculating state vectors from Orbital Elements - C#

Question

I have been working on a project where I want to visualize the orbits in the solar system with the help of Unity Engine. I have been using different guides and similar questions on this forum to construct my code, and I'm closing in into the final solution but i have run into a halt.

When running my code, every variable seems to work properly except eccentricity, which ends up in creating visuals like this.

While running a simple codeblock to plot the 2D ellipse, create this which seemingly looks correct

Now this is the code, and if anyone could help me figure out what im missing in the 3D part i would appreciate it alot!

public void UpdateEllipse()
{
    if (lr == null)
        lr = GetComponent<LineRenderer>();

    lr.positionCount = resolution + 2;

    lr.SetPosition(0,AddPointToLineRenderer( 0));
    for (int i = 1; i <= resolution + 1; i++)
    {
        lr.SetPosition(i, AddPointToLineRenderer(i));
    }
}

Vector3 AddPointToLineRenderer(float index)
{
    Vector3 pointPosition;

    pointPosition = KeplerToCarthesian(index * Mathf.Deg2Rad , semiMajorAxis,eccentrity,argumentofP,longOfAccNode, inclination);

    return pointPosition;        
}

/// <summary>
/// Convert keplarian elements into vector3, needs (Mean Anomaly, Semi Majoris Axis, Eccentricity, Argument of Periapsis, Longitude of Ascending node, Inclination) 
/// </summary>
/// <returns></returns>
Vector3 KeplerToCarthesian(double meanAnomaly , double a, double e, double w, double O, double inc)
{
    //Fix so inlication calculates properly
    inc *= Mathf.Deg2Rad;

    //Gets E and True Anomaly
    E = GetEccentricAnomaly(meanAnomaly, e);
    T = GetTrueAnomaly(e, E) * Mathf.Deg2Rad;

    r = a * (1 - e * Math.Cos(E));

    Vector3 o = new Vector3((float)(r * Math.Cos(T)), (float)(r * Math.Sin(T)), 0);

    double rx, ry, rz;
    rx = o.x; ry = o.y; rz = o.z;

    rx = (o.x * (Math.Cos(w) * Math.Cos(O) - Math.Sin(w) * Math.Cos(inc) * Math.Sin(O)) -
            o.y * (Math.Sin(w) * Math.Cos(O) + Math.Cos(w) * Math.Cos(inc) * Math.Sin(O)));
    ry = (o.x * (Math.Cos(w) * Math.Sin(O) + Math.Sin(w) * Math.Cos(inc) * Math.Cos(O)) +
        o.y * (Math.Cos(w) * Math.Cos(inc) * Math.Cos(O) - Math.Sin(w) * Math.Sin(O)));
    rz = (o.x * (Math.Sin(w) * Math.Sin(inc)) + o.y * (Math.Cos(w) * Math.Sin(inc)));

    //2D Code
    /*double C = Math.Cos(E);
    double S = Math.Sin(E);

    rx = r * (C - e);
    ry = r * Math.Sqrt(1.0 - e * e) * S;
    rz = 0;*/

    return new Vector3((float)rx *10, (float) rz*10, (float) ry*10);
}

private double GetTrueAnomaly(double e, double E)
{
    int dp = 6;
    double phi = Math.Atan2(Math.Sqrt(1 - e) * Math.Cos(E / 2), Math.Sqrt(1 + e) * Math.Sin(E / 2)) / (Math.PI / 180);

    return Math.Round(phi * Math.Pow(10, dp)) / Math.Pow(10, dp);
}

private double GetEccentricAnomaly(double meanAnomaly, double e)
{
    //Solve kepler equation to get Ecentric anomaly
    int tolerance = 6;
    int maxIter = 30, i = 0;
    double delta = Math.Pow(10, -tolerance);
    double E, F;

    meanAnomaly /= 360.0f;

    meanAnomaly = 2.0 * Math.PI * (meanAnomaly - Math.Floor(meanAnomaly));

    if (e < 0.8)
        E = meanAnomaly;
    else
        E = Math.PI;

    F = E - e * Math.Sin(meanAnomaly) - meanAnomaly;

    while ((Math.Abs(F) > delta) && (i < maxIter))
    {

        E = E - F / (1.0 - e * Math.Cos(E));
        F = E - e * Math.Sin(E) - meanAnomaly;
        i++;
    }

    E /= (Math.PI / 180.0);

    return Math.Round(E * Math.Pow(10, tolerance)) / Math.Pow(10, tolerance);
}`