Lift-to-drag ratio

CD and lift CL vs angle of attack. Lift can be created when an aerofoil-shaped body travels through a viscous fluid such as air. The aerofoil is often cambered and/or set at an angle of attack to the airflow. The lift then increases as the square of the airspeed. Whenever an aerodynamic body generates lift, this also creates lift-induced drag or induced drag. At low speeds an aircraft has to generate lift with a higher angle of attack, which results in a greater induced drag. This term dominates the low-speed side of the graph of lift versus velocity. for light aircraft. The tangent gives the maximum 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 drag is more pronounced at greater speeds, forming the right side of the lift/velocity graph's U shape. Profile drag is lowered primarily by streamlining and reducing cross section. The total drag on any aerodynamic body thus has two components, induced drag and form drag. Lift and drag coefficients The rates of change of lift and drag with angle of attack (AoA) are called respectively the lift and drag coefficients CL and CD. The varying ratio of lift to drag with AoA is often plotted in terms of these coefficients. For any given value of lift, the AoA varies with speed. Graphs of CL and CD vs. speed are referred to as drag curves. Speed is shown increasing from left to right. The lift/drag ratio is given by the slope from the origin to some point on the curve and so the maximum L/D ratio does not occur at the point of least drag coefficient, the leftmost point. Instead, it occurs at a slightly greater speed. Designers will typically select a wing design which produces an L/D peak at the chosen cruising speed for a powered fixed-wing aircraft, thereby maximizing economy. Like all things in aeronautical engineering, the lift-to-drag ratio is not the only consideration for wing design. Performance at a high angle of attack and a gentle stall are also important. ==Glide ratio==

As the aircraft fuselage and control surfaces will also add drag and possibly some lift, it is fair to consider the L/D of the aircraft as a whole. The glide ratio, which is the ratio of an (unpowered) aircraft's forward motion to its descent, is (when flown at constant speed) numerically equal to the aircraft's L/D. This is especially of interest in the design and operation of high performance sailplanes, which can have glide ratios almost 60 to 1 (60 units of distance forward for each unit of descent) in the best cases, but with 30:1 being considered good performance for general recreational use. Achieving a glider's best L/D in practice requires precise control of airspeed and smooth and restrained operation of the controls to reduce drag from deflected control surfaces. In zero wind conditions, L/D will equal distance traveled divided by altitude lost. Achieving the maximum distance for altitude lost in wind conditions requires further modification of the best airspeed, as does alternating cruising and thermaling. To achieve high speed across country, glider pilots anticipating strong thermals often load their gliders (sailplanes) with water ballast: the increased wing loading means optimum glide ratio at greater airspeed, but at the cost of climbing more slowly in thermals. As noted below, the maximum L/D is not dependent on weight or wing loading, but with greater wing loading the maximum L/D occurs at a faster airspeed. Also, the faster airspeed means the aircraft will fly at greater Reynolds number and this will usually bring about a lower zero-lift drag coefficient. ==Theory==

Subsonic Mathematically, the maximum lift-to-drag ratio can be estimated as : (L/D)_\text{max} = \frac{1}{2} \sqrt{\frac{\pi \varepsilon \text{AR}}{C_{D,0}}}, where AR is the aspect ratio, \varepsilon the span efficiency factor, a number less than but close to unity for long, straight-edged wings, and C_{D,0} the zero-lift drag coefficient. Most importantly, the maximum lift-to-drag ratio is independent of the weight of the aircraft, the area of the wing, or the wing loading. It can be shown that two main drivers of maximum lift-to-drag ratio for a fixed wing aircraft are wingspan and total wetted area. One method for estimating the zero-lift drag coefficient of an aircraft is the equivalent skin-friction method. For a well designed aircraft, zero-lift drag (or parasite drag) is mostly made up of skin friction drag plus a small percentage of pressure drag caused by flow separation. The method uses the equation : C_{D,0} = C_\text{fe} \frac{S_\text{wet}}{S_\text{ref}}, where C_\text{fe} is the equivalent skin friction coefficient, S_\text{wet} is the wetted area and S_\text{ref} is the wing reference area. The equivalent skin friction coefficient accounts for both separation drag and skin friction drag and is a fairly consistent value for aircraft types of the same class. Substituting this into the equation for maximum lift-to-drag ratio, along with the equation for aspect ratio (b^2/S_\text{ref}), yields the equation (L/D)_\text{max} = \frac{1}{2} \sqrt{\frac{\pi \varepsilon}{C_\text{fe}} \frac{b^2}{S_\text{wet}}}, where b is wingspan. The term b^2/S_\text{wet} is known as the wetted aspect ratio. The equation demonstrates the importance of wetted aspect ratio in achieving an aerodynamically efficient design. Supersonic At supersonic speeds L/D values are lower. Concorde had a lift/drag ratio of about 7 at Mach 2, whereas a 747 has about 17 at about mach 0.85. Dietrich Küchemann developed an empirical relationship for predicting L/D ratio for high Mach numbers: : L/D_\text{max} = \frac{4(M + 3)}{M}, where M is the Mach number. Windtunnel tests have shown this to be approximately accurate. ==Examples of L/D ratios==

has the best glide ratio for a sailplane • House sparrow: 4:1 • Herring gull 10:1 • Common tern 12:1 • Albatross 20:1 • Wright Flyer 8.3:1 • Boeing 747 in cruise 17.7:1. • Cruising Airbus A380 20:1 • Concorde at takeoff and landing 4:1, increasing to 12:1 at Mach 0.95 and 7.5:1 at Mach 2 • Helicopter at 4.5:1 • Cessna 172 gliding 10.9:1 • Rutan Voyager 27:1 • Virgin Atlantic GlobalFlyer 37:1 ==See also==