An experimental study of a 65-degree delta wing with different pitching rates

Al-Garni A., Ahmed S., Sahin A. Z., Al-Garni A.

Canadian Aeronautics and Space Journal, cilt.47, sa.2, ss.85-93, 2001 (Scopus) identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 47 Sayı: 2
  • Basım Tarihi: 2001
  • Dergi Adı: Canadian Aeronautics and Space Journal
  • Derginin Tarandığı İndeksler: Scopus, Academic Search Premier, Aerospace Database, Communication Abstracts, Compendex, Metadex, Civil Engineering Abstracts
  • Sayfa Sayıları: ss.85-93
  • İstanbul Teknik Üniversitesi Adresli: Hayır

Özet

Modern fighter aircraft require high-lift and low-drag forces to maintain their manoeuverability against advances in guided missiles. This paper presents an investigation of the behaviour of a 65-degree swept wing with sharp leading edge under static and dynamic conditions, for low- and high-angle of attack, with more emphasis around the stalling region. The study involves flow visualization and force balance measurement in a wind tunnel. Comparisons of αstall, CL, CLα, CLmax, CD, CL/CD, (CL / CD)max, Cm, and Cmα, are reported for static and dynamic cases. The results show that fast pitch up and slow pitch down motions are recommended for aircraft manoeuvre at high angles of attack to delay stalling and to maintain high-lift and low-drag forces.