Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary
Formula Used
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)
c = (LDEmaxratio*η*ln(WL,beg/WL,end))/(E*VEmax)
This formula uses 1 Functions, 7 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.
Lift to Drag Ratio at Maximum Endurance - Lift to Drag Ratio at Maximum Endurance is the ratio of Lift to Drag at which the plane can fly (or Loiter) for maximum time.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Weight at Start of Loiter Phase - (Measured in Kilogram) - Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase.
Weight at End of Loiter Phase - (Measured in Kilogram) - Weight at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered.
Endurance of Aircraft - (Measured in Second) - Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight.
Velocity for Maximum Endurance - (Measured in Meter per Second) - Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.
STEP 1: Convert Input(s) to Base Unit
Lift to Drag Ratio at Maximum Endurance: 4.4 --> No Conversion Required
Propeller Efficiency: 0.93 --> No Conversion Required
Weight at Start of Loiter Phase: 400 Kilogram --> 400 Kilogram No Conversion Required
Weight at End of Loiter Phase: 394.1 Kilogram --> 394.1 Kilogram No Conversion Required
Endurance of Aircraft: 452.873 Second --> 452.873 Second No Conversion Required
Velocity for Maximum Endurance: 15.6 Meter per Second --> 15.6 Meter per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
c = (LDEmaxratio*η*ln(WL,beg/WL,end))/(E*VEmax) --> (4.4*0.93*ln(400/394.1))/(452.873*15.6)
Evaluating ... ...
c = 8.60695238433325E-06
STEP 3: Convert Result to Output's Unit
8.60695238433325E-06 Kilogram per Second per Watt -->0.0309850285835997 Kilogram per Hour per Watt (Check conversion here)
FINAL ANSWER
0.0309850285835997 0.030985 Kilogram per Hour per Watt <-- Specific Fuel Consumption
(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

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft Formula

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)
c = (LDEmaxratio*η*ln(WL,beg/WL,end))/(E*VEmax)

What do you mean by Endurance of Aircraft?

In aviation, endurance is the maximum length of time that an aircraft can spend in a cruising flight. In other words, it is the amount of time an aircraft can stay in the air with one load of fuel. Endurance is different from range, which is a measure of distance flown. For example, a typical sailplane exhibits high endurance characteristics but poor range characteristics. Endurance can factor into aviation design in a number of ways. Some aircraft, require high endurance characteristics as part of their mission profile (often referred to as loiter time). Endurance plays a prime factor in finding out the fuel fraction for an aircraft. Endurance, like range, is also related to fuel efficiency; fuel-efficient aircraft will tend to exhibit good endurance characteristics.

How to Calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft?

Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft calculator uses 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) to calculate the Specific Fuel Consumption, The Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft formula is defined as the consumption of fuel (by weight) per unit time to produce a certain amount of power. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft using this online calculator? To use this online calculator for Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft, enter Lift to Drag Ratio at Maximum Endurance (LDEmaxratio), Propeller Efficiency (η), Weight at Start of Loiter Phase (WL,beg), Weight at End of Loiter Phase (WL,end), Endurance of Aircraft (E) & Velocity for Maximum Endurance (VEmax) and hit the calculate button. Here is how the Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft calculation can be explained with given input values -> 2159.496 = (4.4*0.93*ln(400/394.1))/(452.873*15.6).

FAQ

What is Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft?
The Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft formula is defined as the consumption of fuel (by weight) per unit time to produce a certain amount of power and is represented as c = (LDEmaxratio*η*ln(WL,beg/WL,end))/(E*VEmax) or 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). Lift to Drag Ratio at Maximum Endurance is the ratio of Lift to Drag at which the plane can fly (or Loiter) for maximum time, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Weight at Start of Loiter Phase is considered as the weight of the plane just before going to loiter phase, Weight at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered, Endurance of aircraft is the maximum length of time that an aircraft can spend in cruising flight & Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.
How to calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft?
The Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft formula is defined as the consumption of fuel (by weight) per unit time to produce a certain amount of power is calculated using 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). To calculate Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft, you need Lift to Drag Ratio at Maximum Endurance (LDEmaxratio), Propeller Efficiency (η), Weight at Start of Loiter Phase (WL,beg), Weight at End of Loiter Phase (WL,end), Endurance of Aircraft (E) & Velocity for Maximum Endurance (VEmax). With our tool, you need to enter the respective value for Lift to Drag Ratio at Maximum Endurance, Propeller Efficiency, Weight at Start of Loiter Phase, Weight at End of Loiter Phase, Endurance of Aircraft & Velocity for Maximum Endurance 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 Lift to Drag Ratio at Maximum Endurance, Propeller Efficiency, Weight at Start of Loiter Phase, Weight at End of Loiter Phase, Endurance of Aircraft & Velocity for Maximum Endurance. 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/Range of aircraft)*(Lift-to-drag ratio)*(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
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