How to Calculate Optimum Range for Prop-Driven Aircraft in Cruising Phase?
Optimum Range for Prop-Driven Aircraft in Cruising Phase calculator uses Range of Aircraft = (Propeller Efficiency*Maximum Lift to Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase) to calculate the Range of Aircraft, The Optimum Range for Prop-Driven Aircraft in Cruising Phase formula is defined as the maximum distance traveled by a propeller-driven plane covered only during the cruise phase of the mission. it is considered that plane is cruising at the maximum lift to drag ratio. Range of Aircraft is denoted by R symbol.
How to calculate Optimum Range for Prop-Driven Aircraft in Cruising Phase using this online calculator? To use this online calculator for Optimum Range for Prop-Driven Aircraft in Cruising Phase, enter Propeller Efficiency (η), Maximum Lift to Drag Ratio of Aircraft (LDmaxratio), Power Specific Fuel Consumption (c), Weight of Aircraft at Beginning of Cruise Phase (Wi) & Weight of Aircraft at End of Cruise Phase (Wf) and hit the calculate button. Here is how the Optimum Range for Prop-Driven Aircraft in Cruising Phase calculation can be explained with given input values -> 0.04207 = (0.93*30)/0.000166666666666667*ln(450/350).