bugs on the shape of pressure distribution when i do single point optimization of the airfoil s809

[EngJamal2023]

Dear Developer,

I hope this letter finds you well. I am writing to request your assistance with a problem I have been experiencing for over a month now. I understand that you may be busy, but I would greatly appreciate any help you can provide.

I have been working on optimizing an airfoil S809 using Python script for Mach Aero. However, I have encountered an issue with the pressure distribution plot at the first iteration. Despite my efforts, I have been unable to find a solution to this problem .but when i increased the mach number the problem is disappear so i need to do my analysis at low mach number without sppear like this problem on the output of cp.

I have carefully analyzed the airfoil and have attached the output file of the mesh, which appears to be in good condition. The distribution around the airfoil also looks good. However, I believe the issue lies with the Python script, as it has not been optimized for Mach Aero.

I would greatly appreciate it if you could provide me with a different Python script that is optimized for Mach Aero. Even one example, such as the tutorial on NACA0012 for single point optimization, would be of immense help.

Thank you for your time and consideration. I look forward to hearing back from you soon.

Sincerely,

Ajlan jamal
master student on Yangzhue University

here the change of the script

mycl = 0.5
# angle of attack
alpha = 1.5
# mach number
mach = 0.1
# cruising altitude
alt = 100 

le = 0.001
# Add objective
optProb.addObj("obj", scale=1.0)

the output i get

the airfoil coordinate that i have

please solve for me this problem how i could solve the error on this plot just give me direct me where i should to focus my effort it will be glad for me to get like this help

[A-CGray]

Mach 0.1 is a very low value to be simulating with a compressible flow solver like ADflow. These spiky Cp distributions are typical of low mach numbers.

2 tips:

• Make sure your mesh is as smooth as possible, try using preFoil to get a smooth distribution of points over your airfoil
• Try using the acousticScaleFactor option in ADflow