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The low speed region shows a fall in lift induced drag, through a minimum followed by an increase in profile drag at higher speeds. The minimum power required, at a speed of 195 km/h (121 mph) is about 86 kW (115 hp); 135 kW (181 hp) is required for a maximum speed of 300 km/h (186 mph). Flight at the power minimum will provide maximum ...
An aircraft flying at this speed is operating at its optimal aerodynamic efficiency. According to the above equations, the speed for minimum drag occurs at the speed where the induced drag is equal to the parasitic drag. [4]: Section 5.25 This is the speed at which for unpowered aircraft, optimum glide angle is achieved.
Maximum brake energy speed [37] [39] V md: Minimum drag (per lift) – often identical to V BE. [35] [39] (alternatively same as V imd [40]) V min: Minimum speed for instrument flight for helicopters [23] V mp: Minimum power [39] V ms: Minimum sink speed at median wing loading – the speed at which the minimum descent rate is obtained.
Drag vs Speed. L/DMAX occurs at minimum Total Drag (e.g. Parasite plus Induced) Coefficients of drag C D and lift C L vs angle of attack. Polar curve showing glide angle for the best glide speed (best L/D). It is the flattest possible glide angle through calm air, which will maximize the distance flown.
In a jet airplane, this is approximately minimum drag speed, occurring at the bottom of the drag vs. speed curve. Climbing at V Y allows pilots to maximize altitude gain per time. 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]
Drag coefficients in fluids with Reynolds number approximately 10 4 [1] [2] Shapes are depicted with the same projected frontal area. In fluid dynamics, the drag coefficient (commonly denoted as: , or ) is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
In supersonic flow regimes, wave drag is commonly separated into two components, supersonic lift-dependent wave drag and supersonic volume-dependent wave drag. The closed form solution for the minimum wave drag of a body of revolution with a fixed length was found by Sears and Haack, and is known as the Sears-Haack Distribution.
These curves show the airspeed where minimum sink can be achieved and the airspeed with the best L/D ratio. The curve is an inverted U-shape. As speeds reduce the amount of lift falls rapidly around the stalling speed. The peak of the 'U' is at minimum drag.