The climb of turbojet aircraft is analyzed and discussed including the accelerations. Three particular flight performances are examined: minimum time of climb, climb with minimum fuel consumption, and steepest climb. The theoretical results obtained from a previous study are put in a form that is suitable for application on the following simplifying assumptions: the Mach number is considered an independent variable instead of the velocity; the variations of the airplane mass due to fuel consumption are disregarded; the airplane polar is assumed to be parabolic; the path curvatures and the squares of the path angles are disregarded in the projection of the equation of motion on the normal to the path; lastly, an ideal turbojet with performance independent of the velocity is involved. The optimum Mach number for each flight condition is obtained from the solution of a sixth order equation in which the coefficients are functions of two fundamental parameters: the ratio of minimum drag in level flight to the thrust and the Mach number which represents the flight at constant altitude and maximum lift-drag ratio.
Optimum flight paths of turbojet aircraft
01.09.1955
Sonstige
Keine Angabe
Englisch
Optimum flight paths of turbojet aircraft
Engineering Index Backfile | 1955
|Approximate solutions to optimum flight trajectories for turbojet-powered aircraft
Engineering Index Backfile | 1959
|Aircraft Optimum Multiple Flight Paths
NTIS | 1970
|Aerodynamics and Flight Dynamics of Turbojet Aircraft
NTIS | 1969
|