Experimental investigation of helicopter fuselage aerodynamics

Abstract

Bu çalışmada rüzgar tüneli deneyleri, ITU Trisonik Araştırma Merkezinin tesisleri kullanılarak yapılmıştır. Eiffel ve Gümüşsüyü rüzgar tünelleri bu çalışmada kullanılmıştır. Helicopter gövdesinin detaylı aerodinamik incelemesi yapılmıştır. Gövde etrafındaki akım niteliksel niceliksel yöntemlerle incelenmiştir. Ayrıca iki farklı gövdeye ait karakteristik aerodinamik katsayılar ve bu katsayıların hücum ve sapma açısıyla nasıl değiştiği deneysel yöntemlerle belirlenmiş, karşılaştırmaları yapılmıştır.

Wind tunnel tests were conducted at the ITU Trisonic Research Center facilities. Eiffel and Gümüşsüyü wind tunnels are used for the experiments. Detailed investigation of isolated helicopter fuselage aerodynamics has been done for this study. Flow around fuselage has been investigated both qualitatively and quantitatively. For qualitative investigation, oil film and smoke flow with laser visualizations have been done. Velocity magnitudes of flow field around fuselage have been measured by CTA system. To determine the aerodynamic characteristics of isolated helicopter fuselage of different configurations, balance measurements have been accomplished. The distribution of aerodynamic coefficients with sideslip angle and incidence angle has been investigated. Comparison of two different configuration fuselage shapes has been done. Results are given after brief explanation of the methods applied, experimental setups and procedures. Images of visualization experiments are given together for different incidence and sideslip angles to be compared. Aerodynamic coefficients are given in graphs together for each configuration to be compared.