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Stalls depend only on angle of attack, not airspeed. [24] However, the slower an aircraft flies, the greater the angle of attack it needs to produce lift equal to the aircraft's weight. [25] As the speed decreases further, at some point this angle will be equal to the critical (stall) angle of attack. This speed is called the "stall speed".
Platform angle of attack Coefficients of drag and lift versus angle of attack. Stall speed corresponds to the angle of attack at the maximum coefficient of lift (C LMAX) A typical lift coefficient curve for an airfoil at a given airspeed. The lift coefficient of a fixed-wing aircraft varies with angle of attack. Increasing angle of attack is ...
The minimum such speed is the stall speed, or V SO. The indicated airspeed at which a fixed-wing aircraft stalls varies with the weight of the aircraft but does not vary significantly with altitude. At speeds close to the stall speed the aircraft's wings are at a high angle of attack. At higher altitudes, the air density is lower than at sea level.
angle of attack α: angle between the x w,y w-plane and the aircraft longitudinal axis and, among other things, is an important variable in determining the magnitude of the force of lift; When performing the rotations described earlier to obtain the body frame from the Earth frame, there is this analogy between angles: β, ψ (sideslip vs yaw)
The stalling angle of attack is less in ground effect, by approximately 2–4 degrees, than in free air. [23] [24] When the flow separates there is a large increase in drag. If the aircraft overrotates on take-off at too low a speed the increased drag can prevent the aircraft from leaving the ground.
The angle at which maximum lift coefficient occurs is the stall angle of the airfoil, which is approximately 10 to 15 degrees on a typical airfoil. The stall angle for a given profile is also increasing with increasing values of the Reynolds number, at higher speeds indeed the flow tends to stay attached to the profile for longer delaying the ...
Above this angle flow over the airfoil becomes detached and lift decreases, a condition commonly called a stall. When a fixed-wing aircraft exceeds its critical angle of attack the entire aircraft loses lift and enters a condition called a stall. The usual consequences of a fixed-wing stall are a sharp drop in aircraft altitude and a dive.
A compressor stall is a local disruption of the airflow in the compressor of a gas turbine or turbocharger. A stall that results in the complete disruption of the airflow through the compressor is referred to as a compressor surge. The severity of the phenomenon ranges from a momentary power drop barely registered by the engine instruments to a ...