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Load factor (aeronautics) In aeronautics, the load factor is the ratio of the lift of an aircraft to its weight [1][2]: § 5.22 and represents a global measure of the stress ("load") to which the structure of the aircraft is subjected: where. is the weight. Since the load factor is the ratio of two forces, it is dimensionless.
A chart of velocity versus load factor (or V-n diagram) is another way of showing limits of aircraft performance. It shows how much load factor can be safely achieved at different airspeeds. [3] At higher temperatures, air is less dense and planes must fly faster to generate the same amount of lift.
Wing loading is a useful measure of the stalling speed of an aircraft. Wings generate lift owing to the motion of air around the wing. Larger wings move more air, so an aircraft with a large wing area relative to its mass (i.e., low wing loading) will have a lower stalling speed.
Speed at which exceeding the limit load factor may cause permanent deformation of the aircraft structure. [7] [8] [9] [24] V O: Maximum operating maneuvering speed. [25] V R: Rotation speed. The speed at which the pilot begins to apply control inputs to cause the aircraft nose to pitch up, after which it will leave the ground. [7] [26] [Note 1 ...
Fuel economy in aircraft. Between 1950 and 2018, efficiency per passenger grew from 0.4 to 8.2 RPK per kg of CO₂. [1] The fuel economy in aircraft is the measure of the transport energy efficiency of aircraft. Fuel efficiency is increased with better aerodynamics and by reducing weight, and with improved engine brake-specific fuel consumption ...
Stall (fluid dynamics) Airflow separating from an airfoil at a high angle of attack, as occurs at a stall. In fluid dynamics, a stall is a reduction in the lift coefficient generated by a foil as angle of attack exceeds its critical value. [1] The critical angle of attack is typically about 15°, but it may vary significantly depending on the ...
In engineering, the ultimate load is a statistical figure used in calculations, and should (hopefully) never actually occur. Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). With respect to aircraft structure and ...
Specifically, the load factor is the dimensionless ratio of passenger-kilometres travelled to seat-kilometres available. For example, say that on a particular day an airline makes 5 scheduled flights, each of which travels 200 kilometers and has 100 seats, and sells 60 tickets for each flight.