University of Technology-IraqEngineering and Technology Journal1681-6900281620100828Control of Separation For NACA 2412 Airfoil At Different Angles of Attack Using Air Blowingالسیطرة على الانفصال لمقطع جناح (NACA 2412) لمختلف زوایا الھجوم باستخدام نفخ الھواء5138515034512ENJalal M. JalilAssim H. YousifYasser Ahmed MahmoodJournal Article20100801The study of the separation control using the jet blowing based on the
computation of Reynolds-average Navier-Stocks equations is carried out in this work. A numerical model based on collocated Finite Volume Method is developed to solve the governing equations on a body-fitted grid, to compute the performance of airfoil by using the blowing jet. Above of all, the performance of turbulence model is investigation. A revised k-ƒÖ model is proposed as the known turbulence models perform well in reproducing the flow of airfoil at pre-stall or stall angle of attack. The systematical investigation of the jet blowing is conducted
on the NACA 2412 airfoil in the range of attack angle from 0o to 30o included up and beyond the stall angle at range of Re=3.4*105-1.7*106 . The influence of some parameters associated with using jet blowing, such as its location, and the speed ratio (Uj/U) strength on the performance of the NACA 2412 airfoil has also been studied. The result shows that the jet blowing is effective in controlling the separation at 0.3C and Uj/U=2. The large separation regions cannot be completely
removed by the jet blowing. However, the flow structure can be regularized. The lift coefficient of the control airfoil is also increased with the angle of the attack. The experimental results are obtained on airfoil NACA 2412 at 0.3C blowing and Uj/U=2, the results are been good agreement with the computational results.https://etj.uotechnology.edu.iq/article_34512_00adb1ed8a16ca6bb4bc9c61eeb72698.pdf