What is Lift to Drag ratio of an aircraft?
In aerodynamics, the lift-to-drag ratio (or L/D ratio) is the lift generated by an aerodynamic body such as an airfoil or aircraft, divided by the aerodynamic drag caused by moving through air. It describes the aerodynamic efficiency under given flight conditions. The L/D ratio for any given body will vary according to these flight conditions. For an airfoil wing or powered aircraft, the L/D is specified when in straight and level flight. For a glider, it determines the glide ratio, of distance traveled against loss of height. The term is calculated for any particular airspeed by measuring the lift generated, then dividing by the drag at that speed. These vary with speed, so the results are typically plotted on a 2-dimensional graph. The L/D may be calculated using computational fluid dynamics or computer simulation. It is measured empirically by testing in a wind tunnel or free-flight test.
How to Calculate Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft?
Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft calculator uses Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase)) to calculate the Maximum Lift to Drag Ratio, The Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft formula is defined as the ratio of the coefficient of lift to the coefficient of drag and considered to be maximum in the magnitude so the range is maximum in the mission plan. Maximum Lift to Drag Ratio is denoted by LDmaxratio symbol.
How to calculate Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft using this online calculator? To use this online calculator for Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft, enter Range of aircraft (R), Specific Fuel Consumption (c), Propeller Efficiency (η), Weight at Start of Cruise Phase (Wi) & Weight at End of Cruise Phase (Wf) and hit the calculate button. Here is how the Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft calculation can be explained with given input values -> 64.66362 = (7126*0.000166666666666667)/(0.93*ln(450/350)).