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The speed for greatest range (i.e. distance travelled) is the speed at which a straight line from the origin is tangent to the fuel flow rate curve. The curve of range versus airspeed is normally very shallow and it is customary to operate at the speed for 99% best range since this gives 3-5% greater speed for only 1% less range.
In aerodynamics, aerodynamic drag, also known as air resistance, is the fluid drag force that acts on any moving solid body in the direction of the air's freestream flow. [ 22 ] From the body's perspective (near-field approach), the drag results from forces due to pressure distributions over the body surface, symbolized D p r {\displaystyle D ...
The deflected or "turned" flow of air creates a resultant force on the wing in the opposite direction (Newton's third law). The resultant force is identified as lift. Flying close to a surface increases air pressure on the lower wing surface, nicknamed the "ram" or "cushion" effect, and thereby improves the aircraft lift-to-drag ratio.
This term dominates the low-speed side of the graph of lift versus velocity. Drag curve for light aircraft. The tangent gives the maximum L/D point. Form drag is caused by movement of the body through air. This type of drag, known also as air resistance or profile drag varies with the square of speed (see drag equation). For this reason profile ...
In 1957 a modified area rule was available for raising the subsonic cruise speed of transport aircraft by 50 mph. [12] The cruise speed is limited by the sudden increase in drag which indicates the presence of local supersonic flow on top of the wing. Whitcomb's modified rule reduced the supersonic speed before the shock, which weakened it and ...
Based on air resistance, for example, the terminal speed of a skydiver in a belly-to-earth (i.e., face down) free fall position is about 55 m/s (180 ft/s). [3] This speed is the asymptotic limiting value of the speed, and the forces acting on the body balance each other more and more closely as the terminal speed is approached. In this example ...
The mathematical formulas that equate to the results of the flight computer wind calculator are as follows: (desired course is d, ground speed is V g, heading is a, true airspeed is V a, wind direction is w, wind speed is V w. d, a and w are angles. V g, V a and V w are consistent units of speed. is approximated as 355/113 or 22/7)
The rate of change of aircraft mass with distance is = =, where is the speed), so that = It follows that the range is obtained from the definite integral below, with t 1 {\displaystyle t_{1}} and t 2 {\displaystyle t_{2}} the start and finish times respectively and W 1 {\displaystyle W_{1}} and W 2 {\displaystyle W_{2}} the initial and final ...