Inverse Aerofoil Optimiser using CST, Python and Xfoil
Budget: £20 – £250 GBP
I'm seeking an expert in aerodynamics and computational fluid dynamics to improve my existing inverted NACA4412 pressure distribution.
Ideally, you will:
- Have extensive experience working with CST, Python and Xfoil.
- Be able to generate an inverse aerofoil that is more efficient than a NACA0012.
- Understand how to manipulate the pressure distribution for optimal performance.
Your goal will be to enhance the aerodynamic performance of the inverted aerofoil, focusing on creating a more uniform pressure distribution. Ultimately, the project aims for a superior lift coefficient, reduced drag and improved stall characteristics.
Ideally, you will:
- Have extensive experience working with CST, Python and Xfoil.
- Be able to generate an inverse aerofoil that is more efficient than a NACA0012.
- Understand how to manipulate the pressure distribution for optimal performance.
Your goal will be to enhance the aerodynamic performance of the inverted aerofoil, focusing on creating a more uniform pressure distribution. Ultimately, the project aims for a superior lift coefficient, reduced drag and improved stall characteristics.
Related categories:
Python
Engineering
Matlab and Mathematica
Mechanical Engineering
Aerospace Engineering