This computational method allows solving inviscid problems for wings with thickness profile. The experimental and numerical results are compared to each other to verify the built program that permits to extend the range of applications with the variation of wing profiles, wing planforms, and incidence angles. | Volume 36 Number 2 2 2014 Vietnam Journal of Mechanics, VAST, Vol. 36, No. 2 (2014), pp. 133 – 143 EXPERIMENTS AND NUMERICAL CALCULATION TO DETERMINE AERODYNAMIC CHARACTERISTICS OF FLOWS AROUND 3D WINGS Nguyen Hong Son1 , Hoang Thi Bich Ngoc2,∗ , Dinh Van Phong2 , Nguyen Manh Hung2 1 Hanoi University of Industry, Vietnam 2 Hanoi University of Science and Technology, Vietnam ∗ E-mail: hoangthibichngoc@ Received October 21, 2013 Abstract. The report presents method and results of experiments in wind tunnel to determine aerodynamic characteristics of 3D wings by measuring pressure distribution on the wing surfaces. Simultaneously, a numerical method by using sources and doublets distributed on panel elements of wing surface also is carried out to calculate flows around 3D wings. This computational method allows solving inviscid problems for wings with thickness profile. The experimental and numerical results are compared to each other to verify the built program that permits to extend the range of applications with the variation of wing profiles, wing planforms, and incidence angles. Keywords: Experiment, singularity method, 3D wing. 1. INTRODUCTION Singularity method using the surface distribution of sources and doublets with constant strength on panel elements is programmed for calculating flows over rectangular wings and trapezoidal wings with small sweep angles at the leading and trailing edges. The method is applied to calculate aerodynamic characteristics of flows around 3D wings in considering the profile thickness with the variation of incidence angles. The singularity method is based on Laplace equation of velocity potential for incompressible and inviscid flow. In the assumption of subsonic flow, incidence angles being not too large and sweep angles of wing having moderate values, results calculated by singularity method and calculated by viscous method are almost no different [1]. In order to verify the built code, the experimental study .
