Uticaj generatora vrtloga na strujno polje oko konvencinalnog delta krila u uslovima podzvučnog strujanja pri većim napadnim uglovima

Shubham Potdar,Manthan Patil,Khushabu Nadaf,Rajesh Gawade,Sanoj Suresh,Devabrata Sahoo

doi:10.5937/fme2102395p

Abstract

Flow over a conventional delta wing has been studied experimentally at a subsonic flow of 20 m/sec and the flow field developed at higher angle of attack varying from 10° to 20° has been captured. A vortex generator is mounted on the leeward surface of the delta wing and its effect on the flow field is studied. The set of wing tip vortices generated over the delta wing is captured by the oil flow visualization and the streamline over the delta wing surface captured with and without a vortex generator are compared. Based on the qualitative results, the effect of the vortex generator on the lift coefficient is anticipated. Further, force measurement is carried out to quantitatively analyze the effect of vortex generator on the lift and drag coefficient experienced by the delta wing and justify the anticipation made out of the qualitative oil flow visualization tests. In the present study, the effect of mounting of a vortex generator is found to be minimal on the lift coefficient experienced by the delta wing. However, a significant reduction in the drag coefficient with increase in angle of attack was observed by mounting a typical vortex generator.

Highlights

With the development of high speed aircraft, the importance of research related to delta wings have increased
The vortex generator is found to have a minimal effect on the lift coefficient at all tested angles of attack
The qualitative results obtained from oil flow visualizations are well justified by the quantitative results obtained by measuring the lift coefficient values

Summary

Introduction

With the development of high speed aircraft, the importance of research related to delta wings have increased. Delta wings are designed for high speed, they still have to take off and land at subsonic speeds This makes it important to study the flow field over a delta wing and its performance in subsonic flow conditions. Delta wing reduces wave drag, in subsonic flight conditions, delta wings are found to be advantageous in terms of lift generation. At higher angle of attack, the vortices generated at the wing tip of the delta wing results in formation of recirculation region on the leeward face of the delta wing. This recirculation region results in the generation of the vortex lift over the delta wing.

Methods

Results

Conclusion