profile drag sentence in Hindi
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- Profile drag is lowered primarily by reducing cross section and streamlining.
- The aerofoil section was a NACA laminar flow one to have a low profile drag.
- The total of the skin-friction drag and the viscosity-related pressure drag is usually called the profile drag.
- In flight, this configuration was found to have a profile drag representative of boundary layer transition at 60 % of chord.
- The lift, and the profile drag, largely due to skin friction which is contributed to by the whole wing area.
- For this reason profile drag is more pronounced at higher speeds, forming the right side of the drag graph's U shape.
- The low speed region shows a fall in lift induced drag, through a minimum followed by an increase in profile drag at higher speeds.
- Collective pitch was an automatic function of throttle setting and profile drag of the propeller, which to maintain rpm diverted torque away from the rotor as airspeed increased.
- Profile drag caused by the deflected ailerons may add further to the difference, along with changes in the lift vectors as one rotates back while the other rotates forward.
- In the as delivered configuration, a profile drag was measured which was representative of the wing section with boundary layer transition at the leading edge ( 0 % laminar flow ).
- "' Skin friction drag "'is a component of profile drag that occurs differently depending on the type of flow over the lifting body ( laminar or turbulent ).
- By excessively deflecting the upward aileron, profile drag is increased rather than reduced and stall at the tip first by limiting the downward aileron deflection and its associated effective increase in angle of attack.
- Profile drag is caused by air hitting the wing, and other parts of the aircraft . This form of drag, also known as wind resistance, varies with the square of speed ( see drag equation ).
- To optimize its function for forward flight, the blades of a tail rotor have no twist to reduce the profile drag, because the tail rotor is mounted with its axis of rotation perpendicular to the direction of flight.
- With thrust being provided by the propellers at cruise speeds, power would be provided to the rotor only to overcome the profile drag of the rotor, operating in a more efficient manner than the freewheeling rotor of an autogyro in autorotation.
- The main issue is that the semi-circular beam wing configuration incurs increased profile drag and weight penalties over a conventional wing of the same lifting planform, and a common straight wing could provide almost the equivalent lift enhancement when exposed to the same slipstream induced increased dynamic pressure.
- At cruise speeds with most or all of the thrust being provided by the propellers, the rotor receives power only sufficient to overcome the profile drag and maintain lift . The effect is a rotorcraft operating in a more efficient manner than the freewheeling rotor of an autogyro in autorotation, minimizing the adverse effects of retreating blade stall of helicopters at higher airspeeds.
- By using the streamwise vector "'i "'parallel to the freestream in place of "'k "'in the integral, we obtain an expression for the pressure drag " D p " ( which includes the pressure portion of the profile drag and, if the wing is three-dimensional, the induced drag ).
- In this case the opposing yaw moment is generated by a difference in profile drag between the left and right wingtips . " Frise ailerons " accentuate this profile drag imbalance by protruding beneath the wing of an upward-deflected aileron, most often by being hinged slightly behind the leading edge and near the bottom of the surface, with the lower section of the aileron surface's leading edge protruding slightly below the wing's undersurface when the aileron is deflected upwards, substantially increasing profile drag on that side.
- In this case the opposing yaw moment is generated by a difference in profile drag between the left and right wingtips . " Frise ailerons " accentuate this profile drag imbalance by protruding beneath the wing of an upward-deflected aileron, most often by being hinged slightly behind the leading edge and near the bottom of the surface, with the lower section of the aileron surface's leading edge protruding slightly below the wing's undersurface when the aileron is deflected upwards, substantially increasing profile drag on that side.
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