The transition from laminar to turbulent flow significantly impacts the separation of the boundary layer and skin friction of the airfoil, ultimately affecting its aerodynamic characteristics. The pressure distribution around the surface of NACA0012 has also been computed at several Reynolds number and ...
The transitional flow past a NACA0012 airfoil at Reynolds numbers, Re, between 50,000 and 140,000 is investigated using experiments and low and high-fidelity numerical simulations. Variations in Reynolds number provide the quasi-steady response of the flow and resulting lift to dynamic inflow (var...
This research paper presents the design and analysis of a NACA 0012 airfoil with a circular dent of 30 mm depth on its upper surface. The objective of this study is to investigate the effect of the dent on the airfoil's aerodynamic performance. The airfoil's geometry was modeled using a ...
Experimental flutter boundaries are presented for a rigid semispan model (NACA 0012 airfoil section) mounted on a flexible mount system. Also, steady and unsteady pressure measurements taken at the flutter condition are presented. The pressure data were acquired over the entire model chord located ...
Keywordsairfoildynamicexperimentpressuremeasurement 目前,由于对改善战斗机机动性的迫切要求,所以就扩大了动态失速的应用范围。 Haper和Flangan早就证明:飞机在做迅速俯仰运动时,可能有相当大的升力增量 1 。南航 曾于1990年用测力法,用扫描法进行数据采集,对NACA0012翼型进行了试验研究 ...
ANSYS CFX仿真介绍 - NACA0012翼型仿真.pdf,17.0 Release Workshop 03: Fluid flow around the NACA0012 Airfoil Introduction to ANSYS CFX 1 © 2016 ANSYS, Inc. July 11, 2016 Introduction Workshop Description: The flow simulated is an external aerodynamics ap
Evaluation of turbulence reduction devices for the Langley 8-foot Transonic Pressure Tunnel C. D. Harris, 2-D aerodynamics characteristics of the NACA 0012 airfoil in the langley 3-foot transonic pressure tunnel, Tech. Mem. NASA-1987-TM-... MO Mckinney,J Scheiman 被引量: 7发表: 1981年 Ku...
usedinpaperisNACA-65-0012airfoilwhichpitchesarounditsleadingedge.Thedistributionof pressureovernumericalairfoilcoincideswiththedesignpressurewellafterseveraliterations.The resultindicatesthestrategyandsolidboundaryconditioninthepaperarereliable. Keywords unsteadyinverseproblem;oscillatingairfoil;unsteadyEulerequations ...
9 display the optimized pressure distribution of the C-type-structured grid geometry for the NACA0012 airfoil [75]. The figures particularly highlight the development of a shock wave on the suction side, occurring between 0.1c and 0.3c of the airfoil's chord length. This is complemented by ...
图8 带不同冰模的NACA0012翼型表面压力系数分布Fig.8 Pressure coefficient distribution along the surface of NACA0012 airfoil with different ice models 表面声功率(Surface Acoustic Power, SAP)WSAP由如下公式计算[27]: (15) 其中,I(y)是表面单位面积的定向声强。是噪声源的表面压力时间导数的均方,由湍流时间...