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A particular aircraft may have different curves even at the same R e and M values, depending for example on whether undercarriage and flaps are deployed. [2] Drag curve for light aircraft. C D0 = 0.017, K = 0.075 and C L0 = 0.1. The tangent gives the maximum L/D point. The accompanying diagram shows C L against C D for a typical light aircraft.
Trim drag, denoted as Dm in the diagram, is the component of aerodynamic drag on an aircraft created by the flight control surfaces, [1] mainly elevators and trimable horizontal stabilizers, when they are used to offset changes in pitching moment and centre of gravity during flight.
The lift-induced drag decreases with the square of velocity. As a result, the total drag (the sum of both components) typically has a minimum value. In practice, the validity of these curves is limited by the occurrence of stall on the left side, and by compressibility effects on the right side.
In aeronautics, air brakes, or speed brakes, are a type of flight control surface used on an aircraft to increase the drag on the aircraft. [1] When extended into the airstream, air brakes cause an increase in the drag on the aircraft. When not in use, they conform to the local streamlined profile of the aircraft in order to help minimize drag. [2]
[1] = where is the aircraft lift coefficient. The lift and drag forces can be applied at a single point, the center of pressure. However, the location of the center of pressure moves significantly with a change in angle of attack and is thus impractical for aerodynamic analysis.
Lift-induced drag, induced drag, vortex drag, or sometimes drag due to lift, in aerodynamics, is an aerodynamic drag force that occurs whenever a moving object redirects the airflow coming at it. This drag force occurs in airplanes due to wings or a lifting body redirecting air to cause lift and also in cars with airfoil wings that redirect air ...
[15] [16] Modifications which included indenting the fuselage beside the wings and adding more volume to the rear of the aircraft, reduced the transonic drag significantly and the Mach 1.2 design speed was reached. The reason for using the area rule on these fighter aircraft was to reduce the peak value of the drag which occurs at Mach 1 and so ...
Generally, the drag coefficient peaks at Mach 1.0 and begins to decrease again after the transition into the supersonic regime above approximately Mach 1.2. The large increase in drag is caused by the formation of a shock wave on the upper surface of the airfoil, which can induce flow separation and adverse pressure gradients on the aft portion ...