Specific Fuel Consumption given Range for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary
Formula Used
Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft
c = (VL/D,max*LDmaxratio*ln(Wi/Wf))/R
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.
Velocity at Maximum Lift to Drag Ratio - (Measured in Meter per Second) - Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.
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.
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.
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.
STEP 1: Convert Input(s) to Base Unit
Velocity at Maximum Lift to Drag Ratio: 50 Meter per Second --> 50 Meter per Second No Conversion Required
Maximum Lift to Drag Ratio: 5.081 --> 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
Range of aircraft: 7126 Meter --> 7126 Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
c = (VL/D,max*LDmaxratio*ln(Wi/Wf))/R --> (50*5.081*ln(450/350))/7126
Evaluating ... ...
c = 0.00895964503294474
STEP 3: Convert Result to Output's Unit
0.00895964503294474 Kilogram per Second per Watt -->32.2547221186011 Kilogram per Hour per Watt (Check conversion here)
FINAL ANSWER
32.2547221186011 โ‰ˆ 32.25472 Kilogram per Hour per Watt <-- Specific Fuel Consumption
(Calculation completed in 00.004 seconds)

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18 Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Range of Jet Airplane
Go Thrust-Specific Fuel Consumption = (sqrt(8/(Freestream density*Reference Area)))*(1/(Range of aircraft*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel)))
Range of Jet Airplane
Go Range of aircraft = (sqrt(8/(Freestream density*Reference Area)))*(1/(Thrust-Specific Fuel Consumption*Drag Coefficient))*(sqrt(Lift Coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel)))
Maximum Lift to Drag Ratio given Range for Jet Aircraft
Go Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Velocity at Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
Specific Fuel Consumption given Range for Jet Aircraft
Go Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft
Breguet Range
Go Range of aircraft = (Lift-to-drag ratio*Flight Velocity*ln(Initial Weight/Final Weight))/([g]*Thrust-Specific Fuel Consumption)
Breguet Endurance Equation
Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*(Lift Coefficient/Drag Coefficient)*ln(Gross Weight/Weight without fuel)
Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane
Go Thrust-Specific Fuel Consumption = Lift Coefficient*(ln(Gross Weight/Weight without fuel))/(Drag Coefficient*Endurance of Aircraft)
Endurance of Jet Airplane
Go Endurance of Aircraft = Lift Coefficient*(ln(Gross Weight/Weight without fuel))/(Drag Coefficient*Thrust-Specific Fuel Consumption)
Cruise Weight Fraction for Jet Aircraft
Go Cruise Weight Fraction = exp((Range of aircraft*Specific Fuel Consumption*(-1))/(0.866*1.32*Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio))
Constant Speed Cruise using Range Equation
Go Range of aircraft = Flight Velocity/(Thrust-Specific Fuel Consumption*Total Thrust)*int(1,x,Weight without fuel,Gross Weight)
Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
Go Lift-to-drag ratio = Specific Fuel Consumption*Range of aircraft/(Propeller Efficiency*ln(Gross Weight/Weight without fuel))
Maximum Lift to Drag Ratio given Preliminary Endurance for Jet Aircraft
Go Maximum Lift to Drag Ratio = (Endurance of Aircraft*Specific Fuel Consumption)/ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase)
Specific Fuel Consumption given Preliminary Endurance for Jet Aircraft
Go Specific Fuel Consumption = (Maximum Lift to Drag Ratio*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/Endurance of Aircraft
Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane
Go Thrust-Specific Fuel Consumption = (1/Endurance of Aircraft)*Lift-to-drag ratio*ln(Gross Weight/Weight without fuel)
Endurance for given Lift-to-Drag ratio of Jet Airplane
Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-drag ratio*ln(Gross Weight/Weight without fuel)
Lift-to-Drag ratio for given Endurance of Jet Airplane
Go Lift-to-drag ratio = Thrust-Specific Fuel Consumption*Endurance of Aircraft/(ln(Gross Weight/Weight without fuel))
Loiter Weight Fraction for Jet Aircraft
Go Loiter weight Fraction for Jet aircraft = exp(((-1)*Endurance of Aircraft*Specific Fuel Consumption)/Maximum Lift to Drag Ratio)
Average Value Range Equation
Go Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity))

Specific Fuel Consumption given Range for Jet Aircraft Formula

Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft
c = (VL/D,max*LDmaxratio*ln(Wi/Wf))/R

What is Specific Fuel Consumption?

The Specific Fuel Consumption (SFC) is a technical figure of merit for an engine that indicates how efficiently the engine is burning fuel and converting it to thrust. SFC depends on the type and design technology of the engine and also the type of fuel. SFC is used to describe the fuel efficiency of an engine with respect to its mechanical output.

How to Calculate Specific Fuel Consumption given Range for Jet Aircraft?

Specific Fuel Consumption given Range for Jet Aircraft calculator uses Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft to calculate the Specific Fuel Consumption, The Specific Fuel Consumption given Range for Jet Aircraft formula is defined as the fuel consumed by the engine over a unit of time to produce a specific amount of thrust. Specific Fuel Consumption is denoted by c symbol.

How to calculate Specific Fuel Consumption given Range for Jet Aircraft using this online calculator? To use this online calculator for Specific Fuel Consumption given Range for Jet Aircraft, enter Velocity at Maximum Lift to Drag Ratio (VL/D,max), Maximum Lift to Drag Ratio (LDmaxratio), Weight at Start of Cruise Phase (Wi), Weight at End of Cruise Phase (Wf) & Range of aircraft (R) and hit the calculate button. Here is how the Specific Fuel Consumption given Range for Jet Aircraft calculation can be explained with given input values -> 9124.939 = (50*5.081*ln(450/350))/7126.

FAQ

What is Specific Fuel Consumption given Range for Jet Aircraft?
The Specific Fuel Consumption given Range for Jet Aircraft formula is defined as the fuel consumed by the engine over a unit of time to produce a specific amount of thrust and is represented as c = (VL/D,max*LDmaxratio*ln(Wi/Wf))/R or Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft. Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase, Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value, 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 & Range of aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
How to calculate Specific Fuel Consumption given Range for Jet Aircraft?
The Specific Fuel Consumption given Range for Jet Aircraft formula is defined as the fuel consumed by the engine over a unit of time to produce a specific amount of thrust is calculated using Specific Fuel Consumption = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft. To calculate Specific Fuel Consumption given Range for Jet Aircraft, you need Velocity at Maximum Lift to Drag Ratio (VL/D,max), Maximum Lift to Drag Ratio (LDmaxratio), Weight at Start of Cruise Phase (Wi), Weight at End of Cruise Phase (Wf) & Range of aircraft (R). With our tool, you need to enter the respective value for Velocity at Maximum Lift to Drag Ratio, Maximum Lift to Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of aircraft 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 Velocity at Maximum Lift to Drag Ratio, Maximum Lift to Drag Ratio, Weight at Start of Cruise Phase, Weight at End of Cruise Phase & Range of aircraft. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Specific Fuel Consumption = (Maximum Lift to Drag Ratio*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/Endurance of Aircraft
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