Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane Solution

STEP 0: Pre-Calculation Summary
Formula Used
Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
c = (η/R)*(LD)*(ln(W0/W1))
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
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).
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.
Lift-to-drag ratio - The Lift-to-drag ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.
Gross Weight - (Measured in Kilogram) - The Gross Weight of the airplane is the weight with full fuel and payload.
Weight without fuel - (Measured in Kilogram) - Weight without fuel is the total weight of the airplane without fuel.
STEP 1: Convert Input(s) to Base Unit
Propeller Efficiency: 0.93 --> No Conversion Required
Range of aircraft: 7126 Meter --> 7126 Meter No Conversion Required
Lift-to-drag ratio: 2.5 --> No Conversion Required
Gross Weight: 5000 Kilogram --> 5000 Kilogram No Conversion Required
Weight without fuel: 3000 Kilogram --> 3000 Kilogram No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
c = (η/R)*(LD)*(ln(W0/W1)) --> (0.93/7126)*(2.5)*(ln(5000/3000))
Evaluating ... ...
c = 0.000166667074832435
STEP 3: Convert Result to Output's Unit
0.000166667074832435 Kilogram per Second per Watt -->0.600001469396764 Kilogram per Hour per Watt (Check conversion here)
FINAL ANSWER
0.600001469396764 0.600001 Kilogram per Hour per Watt <-- Specific Fuel Consumption
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Verified by Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 300+ more calculators!

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

Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane Formula

Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
c = (η/R)*(LD)*(ln(W0/W1))

Is the maximum lift-to-drag ratio affected by the weight of the aircraft?

The maximum lift-to-drag ratio is independent of the weight of the aircraft, the area of the wing, or the wing loading.

How to Calculate Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane?

Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane calculator uses Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel)) to calculate the Specific Fuel Consumption, The Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane is obtained from the Breguet range formula and is a function of propeller efficiency, gross weight, and weight without the fuel of aircraft. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane using this online calculator? To use this online calculator for Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane, enter Propeller Efficiency (η), Range of aircraft (R), Lift-to-drag ratio (LD), Gross Weight (W0) & Weight without fuel (W1) and hit the calculate button. Here is how the Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane calculation can be explained with given input values -> 14688.04 = (0.93/7126)*(2.5)*(ln(5000/3000)).

FAQ

What is Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane?
The Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane is obtained from the Breguet range formula and is a function of propeller efficiency, gross weight, and weight without the fuel of aircraft and is represented as c = (η/R)*(LD)*(ln(W0/W1)) or Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel)). Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, The Lift-to-drag ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air, The Gross Weight of the airplane is the weight with full fuel and payload & Weight without fuel is the total weight of the airplane without fuel.
How to calculate Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane?
The Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane is obtained from the Breguet range formula and is a function of propeller efficiency, gross weight, and weight without the fuel of aircraft is calculated using Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel)). To calculate Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane, you need Propeller Efficiency (η), Range of aircraft (R), Lift-to-drag ratio (LD), Gross Weight (W0) & Weight without fuel (W1). With our tool, you need to enter the respective value for Propeller Efficiency, Range of aircraft, Lift-to-drag ratio, Gross Weight & Weight without fuel 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 Specific Fuel Consumption?
In this formula, Specific Fuel Consumption uses Propeller Efficiency, Range of aircraft, Lift-to-drag ratio, Gross Weight & Weight without fuel. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
  • 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))
  • 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 = (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)
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!