Sukhoi SU-47 Berkut and Eurofighter Typhoon Models Flow Visualization and Performance Investigation Using GAMA Water Tunnel

Febryanto Nugroho,Sigit Iswahyudi,Yogi Adi Pratama,Sutrisno .,Setyawan Bekti Wibowo

doi:10.5539/mas.v13n2p21

Abstract

Changes and modifications to the wings of fighter aircraft were carried out, one of which was the forward swept wing which was a moderate wing that continues to develop. There were also types of delta wings that had been applied to many fighter planes. Both types of aircraft wings had certainly different aerodynamic characteristics. This research would study the flow visualization that occurs in the aircraft model body to determine the aerodynamic characteristics of the forward swept wing and delta wing. This study used a water tunnel to observe the aerodynamic flow and forces that occurred in both types of wings. This visualization test used similar aircraft models: SU-47 Berkut and Eurofighter Typhoon. The results provided flow visualization, coefficient of lift (Cl), and coefficient of drag (Cd) which showed that the stall that occurred on the aircraft model similar to the SU-47 Berkut occurred at an angle of attack (AoA) 500 with a Cl max value of 2.66. Meanwhile, the Eurofighter Typhoon stall model occurred at an angle of attack 450 with a Cl max value of 1.48.

Highlights

The aerodynamic design of an aircraft continues progressing since its introduction in the 1920s
This study focuses on observing the effect of fuselage variations on vortex dynamics and aerodynamic performance on aircraft models similar to the Sukhoi Su-30MKI using GAMA water tunnel
By using the GAMA Water Tunnel facility, we have obtained the results of flow visualization, the coefficient of lift (Cl) value, and coefficient of drag (Cd) value

Summary

Introduction

The aerodynamic design of an aircraft continues progressing since its introduction in the 1920s. At high-speed conditions, precise aircraft design is significant to reduce the total drag of an aircraft and improve flight performance (Simpson, 2001) Airplane performance, such as maximum flight speed or fuel consumption, depends on the drag and lift coefficient which can be improved with better aerodynamic design (Della Vecchia & Nicolosi, 2014). One of the essential items in the aerodynamic design of a plane is the meeting between the wing and body This meeting was identified as a body relationship with different aircraft components, in the particulars of the wing and body shape of the aircraft. This meeting induces interactions between components, especially the combined boundary layer which causes flow phenomena to be complicated to explain and simulate (Simpson, 2001)

Methods

Discussion

Conclusion