Wing Design for HSUAV for Endurance Performance with Pitching Moment Constraint

Authors

  • Satish Chander Gupta Professor and Head, Department of Aeronautical Engineering, MVJ College of Engineering, Bangalore, Karnataka, India.
  • Megha B PG Student, Department of Aeronautical Engineering, MVJ College of Engineering, Bangalore, Karnataka, India.

Keywords:

Endurance performance, Elevons/ elevators, HSUAV

Abstract

Wing design for High Speed Unmanned Air Vehicle (HSUAV) for endurance performance is worked out. High loitering lift coefficient demands maximum lift with minimum drag. The design to meet this requirement is seen to result in large negative pitching moment that has to be balanced though deflected up elevons/ elevators, which is drag penalizing. In our approach, the maximum lift to drag ratio at increased value of lift coefficient with constraint on resulting pitching moment is worked out. The pitching moment is constrained to specified values and lift is incremented till the endurance criterion is met.

References

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Published

2019-01-05

Issue

Vol. 4 No. 3 (2017): Journal of Advanced Research in Aeronautics and Space Science

Section

Research Article