Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft Solution

STEP 0: Pre-Calculation Summary
Formula Used
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))
LDmaxratio = (R*c)/(η*ln(Wi/Wf))
This formula uses 1 Functions, 6 Variables
Functions Used
ln - The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function., ln(Number)
Variables Used
Maximum Lift to Drag Ratio - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
Range of aircraft - (Measured in Meter) - Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Weight at Start of Cruise Phase - (Measured in Kilogram) - Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.
Weight at End of Cruise Phase - (Measured in Kilogram) - Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.
STEP 1: Convert Input(s) to Base Unit
Range of aircraft: 7126 Meter --> 7126 Meter No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Propeller Efficiency: 0.93 --> No Conversion Required
Weight at Start of Cruise Phase: 450 Kilogram --> 450 Kilogram No Conversion Required
Weight at End of Cruise Phase: 350 Kilogram --> 350 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
LDmaxratio = (R*c)/(η*ln(Wi/Wf)) --> (7126*0.000166666666666667)/(0.93*ln(450/350))
Evaluating ... ...
LDmaxratio = 5.08152651893194
STEP 3: Convert Result to Output's Unit
5.08152651893194 --> No Conversion Required
FINAL ANSWER
5.08152651893194 5.081527 <-- Maximum Lift to Drag Ratio
(Calculation completed in 00.004 seconds)

Credits

Created by Vedant Chitte
All India Shri Shivaji Memorials Society's ,College of Engineering (AISSMS COE PUNE), Pune
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21 Propeller-Driven Airplane Calculators

Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Go Propeller Efficiency = Endurance of Aircraft/((1/Specific Fuel Consumption)*((Lift Coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Weight without fuel)^(1/2))-((1/Gross Weight)^(1/2))))
Endurance of Propeller-Driven Airplane
Go Endurance of Aircraft = Propeller Efficiency/Specific Fuel Consumption*(Lift Coefficient^1.5)/Drag Coefficient*sqrt(2*Freestream density*Reference Area)*((1/Weight without fuel)^(1/2)-(1/Gross Weight)^(1/2))
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Go Specific Fuel Consumption = Propeller Efficiency/Endurance of Aircraft*Lift Coefficient^1.5/Drag Coefficient*sqrt(2*Freestream density*Reference Area)*((1/Weight without fuel)^(1/2)-(1/Gross Weight)^(1/2))
Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft
Go Lift to Drag Ratio at Maximum Endurance = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))
Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft
Go Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance)
Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft
Go Propeller Efficiency = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Lift to Drag Ratio at Maximum Endurance*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))
Specific Fuel Consumption for given Range of Propeller-Driven Airplane
Go Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
Range of Propeller-Driven Airplane
Go Range of aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
Propeller Efficiency for given Range of Propeller-Driven Airplane
Go Propeller Efficiency = Range of aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without fuel))
Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft
Go 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))
Propeller Efficiency given Range for Prop-Driven Aircraft
Go Propeller Efficiency = (Range of aircraft*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
Specific Fuel Consumption given Range for Prop-Driven Aircraft
Go Specific Fuel Consumption = (Propeller Efficiency*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft
Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
Range of Propeller-Driven Airplane for given lift-to-drag ratio
Go Range of aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go Propeller Efficiency = Range of aircraft*Specific Fuel Consumption/(Lift-to-drag ratio*(ln(Gross Weight/Weight without fuel)))
Cruise Weight Fraction for Prop-Driven Aircraft
Go Cruise Weight Fraction = exp((Range of aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*Propeller Efficiency))
Propeller efficiency for reciprocating engine-propeller combination
Go Propeller Efficiency = Available Power/Brake Power
Shaft brake power for reciprocating engine-propeller combination
Go Brake Power = Available Power/Propeller Efficiency
Power available for reciprocating engine-propeller combination
Go Available Power = Propeller Efficiency*Brake Power
Lift to Drag Ratio for Maximum Endurance given Max Lift to Drag Ratio for Prop-driven Aircraft
Go Lift to Drag Ratio at Maximum Endurance = 0.866*Maximum Lift to Drag Ratio
Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft
Go Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866

Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft Formula

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))
LDmaxratio = (R*c)/(η*ln(Wi/Wf))

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)).

FAQ

What is Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft?
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 and is represented as LDmaxratio = (R*c)/(η*ln(Wi/Wf)) or 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)). Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Weight at Start of Cruise Phase is the weight of the plane just before going to cruise phase of the mission & Weight at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.
How to calculate Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft?
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 is calculated using 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 Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft, you need 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). With our tool, you need to enter the respective value for Range of aircraft, Specific Fuel Consumption, Propeller Efficiency, Weight at Start of Cruise Phase & Weight at End of Cruise Phase and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Maximum Lift to Drag Ratio?
In this formula, Maximum Lift to Drag Ratio uses Range of aircraft, Specific Fuel Consumption, Propeller Efficiency, Weight at Start of Cruise Phase & Weight at End of Cruise Phase. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866
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