Abstract
Numerical Investigation of a Pitching NACA 0012 Wing with Plasma-Based Flow Control Using Prediction–Correction Direct-Forcing Immersed Boundary Method
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
