Comparison of generalized approximate cruise range solutions for turbojet/fan aircraft

Cavcar M., Cavcar A.

JOURNAL OF AIRCRAFT, vol.40, no.5, pp.891-895, 2003 (SCI-Expanded) identifier identifier

  • Publication Type: Article / Article
  • Volume: 40 Issue: 5
  • Publication Date: 2003
  • Doi Number: 10.2514/2.6879
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Page Numbers: pp.891-895
  • Anadolu University Affiliated: No


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.