Journal of the Korea Institute of Military Science and Technology (한국군사과학기술학회지)

The Korea Institute of Military Science and Technology (한국군사과학기술학회)
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Stability and Control Characteristic Analysis of Tailless Delta Wing Aircraft through Pilot Wind-Tunnel Test

파일롯 풍동시험을 통한 무미익 델타형 항공기 조종안정성 분석

  • Heungsik Lim (Flight Control Lab., Aerospace Technology Research Institute, Agency for Defense Development) ;
  • Gibong Hur (Flight Control Lab., Aerospace Technology Research Institute, Agency for Defense Development) ;
  • Jinsung Hong (Department of Aeronautical & Mechanical Engineering, Inha Technical College)
  • 임흥식 (국방과학연구소 항공기술연구원 비행제어팀) ;
  • 허기봉 (국방과학연구소 항공기술연구원 비행제어팀) ;
  • 홍진성 (인하공업전문대학 항공기계공학과)
  • Received : 2024.09.04
  • Accepted : 2024.12.13
  • Published : 2025.02.05
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Abstract

This paper contains the pilot wind tunnel test result of a scaled model to figure out the aerodynamic characteristics in the initial design phase. The initial model is designed as tailless delta wing type. Many papers dealt with the characteristics of this kind of aircraft and the wind tunnel test result performed coincides with these results. Basically, this type of aircraft does not have a horizontal tail and vertical tail, it shows unstability in either lateral/directional axis and longitudinal axis as well. It also shows abrupt increase in pitching moment over a certain angle of attack, which means the Flight Control Law would be designed very carefully to fly the aircraft safely and effectively.

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Acknowledgement

이 논문은 정부의 재원으로 수행된 연구 결과임 (UI912240201).

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