Comparison of generalized approximate cruise range solutions for turbojet/fan aircraft
JOURNAL OF AIRCRAFT, cilt.40, sa.5, ss.891-895, 2003 (SCI-Expanded, Scopus)
- Yayın Türü: Makale / Tam Makale
- Cilt numarası: 40 Sayı: 5
- Basım Tarihi: 2003
- Doi Numarası: 10.2514/2.6879
- Dergi Adı: JOURNAL OF AIRCRAFT
- Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus
- Sayfa Sayıları: ss.891-895
- Anadolu Üniversitesi Adresli: Hayır
Özet
Two different approximate solutions are proposed and compared with the numerical solution of the constant-altitude-constant-Mach-number cruise range for turbojet/fan aircraft. The approximate solutions consider both cambered wing drag polar and dependence of specific fuel consumption on Mach number. It is also proved that the classical analytical approach assuming constant specific fuel consumption and uncambered wing drag polar results in higher optimum Mach numbers and shorter ranges for constant-altitude-constant-airspeed flight of turbojet/fan transport aircraft.