- The document contains aerodynamic data for the 20-32C airfoil profile calculated using XFOIL software.
- It provides values for lift coefficient (CL), drag coefficient (CD), pressure drag coefficient (CDp), moment coefficient (CM), and boundary layer transition locations on the top and bottom of the airfoil over a range of angles of attack from -12.75 to 12.75 degrees.
- The calculations were performed at a Reynolds number of 100,000 and zero Mach number.
- The document contains aerodynamic data for the 20-32C airfoil profile calculated using XFOIL software.
- It provides values for lift coefficient (CL), drag coefficient (CD), pressure drag coefficient (CDp), moment coefficient (CM), and boundary layer transition locations on the top and bottom of the airfoil over a range of angles of attack from -12.75 to 12.75 degrees.
- The calculations were performed at a Reynolds number of 100,000 and zero Mach number.
- The document contains aerodynamic data for the 20-32C airfoil profile calculated using XFOIL software.
- It provides values for lift coefficient (CL), drag coefficient (CD), pressure drag coefficient (CDp), moment coefficient (CM), and boundary layer transition locations on the top and bottom of the airfoil over a range of angles of attack from -12.75 to 12.75 degrees.
- The calculations were performed at a Reynolds number of 100,000 and zero Mach number.
- The document contains aerodynamic data for the 20-32C airfoil profile calculated using XFOIL software.
- It provides values for lift coefficient (CL), drag coefficient (CD), pressure drag coefficient (CDp), moment coefficient (CM), and boundary layer transition locations on the top and bottom of the airfoil over a range of angles of attack from -12.75 to 12.75 degrees.
- The calculations were performed at a Reynolds number of 100,000 and zero Mach number.