I am simulating NACA 2415 Airfoil for different Reynolds Number i.e. 2 million,3 million and 4 million on ANSYS Fluent. The difference between the critical Angle of attack is quite vast. For the 4 million Re number, I am getting a critical Angle of attack close to 46 degrees which seems to be very weird and looks incorrect to me. Any explaination of how different the critical Angle of attacks would be for the above mentioned Reynolds Number?