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The airflow from above and below the wing rejoins downwind of the stagnation point. This is in accordance with the Kutta-Joukowski condition. A forward stagnation point also exists. See Diagram 65, Pressure Differential & Stagnation Points. Aileron drag The ailerons produce drag when deflected either up or down into the air stream. Drag maybe asymmetric being greater on the up-rolling wing where the total reaction is tilted rearwards causing the rearward component to produce increased drag and retard the wing from turning.
The other two bases are Langley Research Centre in Virginia and Lewis Research Centre, renamed the John H. Glen Research Centre at Lewis Field in Cleveland, Ohio. The NASA Space Shuttles were also tested at the Ames Research Centre along with other manned space vehicles. See Wind tunnels. Angle of advance The angle of advance of a propeller blade is related to the helix angle. Diagram 68, Propeller Pitch, shows the helix angle AB-AC. Angle of attack (α) The angle between the free stream relative airflow (RAF) and the wing’s chord line is the angle of attack.
Maximum dynamic pressure occurs at the wing’s leading edge known as the stagnation point. The airflow over the upper wing surface decreases in pressure with a corresponding relative increase in positive pressure underneath the wing. The difference in pressure between the upper and lower surface is responsible for lift. At the wing’s point of maximum camber and at large angles of attack, the centripetal force of the curving airflow is also at a maximum. With a further increase in angle of attack, the flow will eventually depart the upper surface at a tangent and breakaway to form a turbulent flow with a partial loss of lift (a stall).