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At Mach 0.85 and 0.7 lift coefficient, a wing loading of 50 lb/sq ft (240 kg/m 2) can reach a structural limit of 7.33g up to 15,000 feet (4,600 m) and then decreases to 2.3g at 40,000 feet (12,000 m). With a wing loading of 100 lb/sq ft (490 kg/m 2) the load factor is twice smaller and barely reaches 1g at 40,000 ft (12,000 m). [15]
A radio-controlled aircraft (often called RC aircraft or RC plane) is a small flying machine that is radio controlled by an operator on the ground using a hand-held radio transmitter. The transmitter continuously communicates with a receiver within the craft that sends signals to servomechanisms (servos) which move the control surfaces based on ...
In the definition of load factor, the lift is not simply that one generated by the aircraft's wing, instead it is the vector sum of the lift generated by the wing, the fuselage and the tailplane, [2]: 395 or in other words it is the component perpendicular to the airflow of the sum of all aerodynamic forces acting on the aircraft.
A "kill" is only scored when one plane is grounded and the other flies away, regardless of which plane initiated the hit. Expanded polypropylene foam (EPP) foam has become very popular in the construction of these gliders, primarily due to their damage resistance and low cost. The most common wing span is 4 feet (1.2 meters).
In a stall turn the plane goes upward, decelerates, yaws 180° under stall, and comes down nearly the same path it goes up, as if it gets hammered on the head. To perform a stall turn; From level flight input up elevator and reduce power until the aircraft stalls. The angle, speed, and abruptness at which stall occurs depends on the aircraft.
Thus, a long, narrow wing has a high aspect ratio, whereas a short, wide wing has a low aspect ratio. [ 1 ] Aspect ratio and other features of the planform are often used to predict the aerodynamic efficiency of a wing because the lift-to-drag ratio increases with aspect ratio, improving the fuel economy in powered airplanes and the gliding ...
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.
Most importantly, the maximum lift-to-drag ratio is independent of the weight of the aircraft, the area of the wing, or the wing loading. It can be shown that two main drivers of maximum lift-to-drag ratio for a fixed wing aircraft are wingspan and total wetted area. One method for estimating the zero-lift drag coefficient of an aircraft is the ...