LAMINAR STABILITY ANALYSIS IN BOUNDARY LAYER FLOW

This study presents a numerical study concerning the flow control by suction and injection. The case study is over a symmetrical airfoil with suction and injection slots. The angle of attack is 3 degree with the Mach number 0.12.

Bibliographic Details
Main Author: Mihaela CALUDESCU
Format: Article
Language:English
Published: National Institute for Aerospace Research “Elie Carafoli” - INCAS 2009-09-01
Series:INCAS Bulletin
Online Access:http://bulletin.incas.ro/files/mihaela_caludescu_v1no1_full.pdf

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