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The service ceiling is the maximum altitude of an aircraft during normal operations. Specifically, it is the density altitude at which flying in a clean configuration , at the best rate of climb airspeed for that altitude and with all engines operating and producing maximum continuous power, will produce a given rate of climb.
As the aircraft gains altitude the stall speed increases; since the wing is not growing any larger the only way to support the aircraft's weight with less air is to increase speed. While the exact numbers will vary widely from aircraft to aircraft, the nature of this relationship is typically the same; plotted on a graph of speed (x-axis) vs ...
This occurs at the speed where the difference between engine power and the power required to overcome the aircraft's drag is greatest (maximum excess power). [3] V x increases with altitude and V Y decreases with altitude until they converge at the airplane's absolute ceiling, the altitude above which the airplane cannot climb in steady flight.
On 7 May 1958, the aircraft reached an altitude of 27,812 m (91,247 ft) in a zoom climb at Edwards Air Force Base, setting a new altitude record. The Mach 2 mission took the airplane so high that the standard F-104's engine routinely exceeded its temperature limit and had to be shut down. Sometimes the engine simply flamed out for lack of air.
The minimum speed that the aircraft is still controllable with the critical engine inoperative [21] while the aircraft is on the ground. V MCL: Minimum control speed in the landing configuration with one engine inoperative. [9] [21] V MO: Maximum operating limit speed. [7] [8] [9] Exceeding V MO may trigger an overspeed alarm. [22] V MU ...
The rate of change of aircraft mass with distance is = =, where is the speed), so that = It follows that the range is obtained from the definite integral below, with t 1 {\displaystyle t_{1}} and t 2 {\displaystyle t_{2}} the start and finish times respectively and W 1 {\displaystyle W_{1}} and W 2 {\displaystyle W_{2}} the initial and final ...
Coffin corner (also known as the aerodynamic ceiling [1] or Q corner) is the region of flight where a fast but subsonic fixed-wing aircraft's stall speed is near the critical Mach number, making it very difficult to keep an airplane in stable flight. Because the stall speed is the minimum speed required to maintain level flight, any reduction ...
where a 0 is 1,225 km/h (661.45 kn) (the standard speed of sound at 15 °C), M is the Mach number, P is static pressure, and P 0 is standard sea level pressure (1013.25 hPa). Combining the above with the expression for Mach number gives EAS as a function of impact pressure and static pressure (valid for subsonic flow):