Cruise Weight Fraction for Prop-Driven Aircraft Calculator

✖Range of Propeller Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of Propeller Aircraft [R_prop]			+10% -10%
✖Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Specific Fuel Consumption [c]			+10% -10%
✖The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.ⓘ Maximum Lift-to-Drag Ratio [LDmax_ratio]			+10% -10%
✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%

✖Cruise Weight Fraction Propeller Aircraft is the ratio of the weight of aircraft at the end of cruise phase to the weight of aircraft at the start of cruise phase.ⓘ Cruise Weight Fraction for Prop-Driven Aircraft [FW_{cruise prop}]

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Formula

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Cruise Weight Fraction for Prop-Driven Aircraft

Formula

FW cruise prop = \exp (\frac{R prop \cdot (- 1) \cdot c}{LDmax ratio \cdot η})

Example

0.777777 = \exp (\frac{7126.017 m \cdot (- 1) \cdot 0.6 kg/h/W}{5.081527 \cdot 0.93})

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Cruise Weight Fraction for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Cruise Weight Fraction Propeller Aircraft = exp((Range of Propeller Aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*Propeller Efficiency))
FW_{cruise prop} = exp((R_prop*(-1)*c)/(LDmax_ratio*η))
This formula uses 1 Functions, 5 Variables

Functions Used

exp - n an exponential function, the value of the function changes by a constant factor for every unit change in the independent variable., exp(Number)

Variables Used

Cruise Weight Fraction Propeller Aircraft - Cruise Weight Fraction Propeller Aircraft is the ratio of the weight of aircraft at the end of cruise phase to the weight of aircraft at the start of cruise phase.
Range of Propeller Aircraft - (Measured in Meter) - Range of Propeller 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.
Maximum Lift-to-Drag Ratio - The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).

STEP 1: Convert Input(s) to Base Unit

Range of Propeller Aircraft: 7126.017 Meter --> 7126.017 Meter No Conversion Required
Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Maximum Lift-to-Drag Ratio: 5.081527 --> No Conversion Required
Propeller Efficiency: 0.93 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

FW_{cruise prop} = exp((R_prop*(-1)*c)/(LDmax_ratio*η)) --> exp((7126.017*(-1)*0.000166666666666667)/(5.081527*0.93))

Evaluating ... ...

FW_{cruise prop} = 0.777777329971361

STEP 3: Convert Result to Output's Unit

0.777777329971361 --> No Conversion Required

FINAL ANSWER

0.777777329971361 ≈ 0.777777 <-- Cruise Weight Fraction Propeller Aircraft

(Calculation completed in 00.004 seconds)

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Created by Vedant Chitte

All India Shri Shivaji Memorials Society's ,College of Engineering (AISSMS COE PUNE), Pune

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< Propeller Driven Airplane Calculators

Specific Fuel Consumption for given Range of Propeller-Driven Airplane

Go Specific Fuel Consumption = (Propeller Efficiency/Range of Propeller Aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without Fuel))

Range of Propeller-Driven Airplane

Go Range of Propeller 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 Propeller Aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without Fuel))

Range of Propeller-Driven Airplane for given lift-to-drag ratio

Go Range of Propeller Aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-Drag Ratio)*(ln(Gross Weight/Weight without Fuel))

Cruise Weight Fraction for Prop-Driven Aircraft Formula

What is Cruise Weight Fraction?

The Cruise Weight Fraction is defined as the ratio of the weight of the Aircraft at the End of Cruise Phase to the Weight of Aircraft at the Start of Cruise phase. It depends upon the range of aircraft, the Specific Fuel Consumption of the engine, it also depends upon the Propeller Efficiency and the maximum Lift to Drag Ratio itself.
It is Basically important for the preliminary estimation of Take Off Weight.

How to Calculate Cruise Weight Fraction for Prop-Driven Aircraft?

Cruise Weight Fraction for Prop-Driven Aircraft calculator uses Cruise Weight Fraction Propeller Aircraft = exp((Range of Propeller Aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*Propeller Efficiency)) to calculate the Cruise Weight Fraction Propeller Aircraft, Cruise Weight Fraction for Prop-Driven Aircraft is a measure that estimates the proportion of an aircraft's weight during cruise, which is influenced by the range of the propeller aircraft, specific fuel consumption, maximum lift-to-drag ratio, and propeller efficiency, providing a crucial parameter in aircraft design and performance optimization. Cruise Weight Fraction Propeller Aircraft is denoted by FW_{cruise prop} symbol.

How to calculate Cruise Weight Fraction for Prop-Driven Aircraft using this online calculator? To use this online calculator for Cruise Weight Fraction for Prop-Driven Aircraft, enter Range of Propeller Aircraft (R_prop), Specific Fuel Consumption (c), Maximum Lift-to-Drag Ratio (LDmax_ratio) & Propeller Efficiency (η) and hit the calculate button. Here is how the Cruise Weight Fraction for Prop-Driven Aircraft calculation can be explained with given input values -> 0.777777 = exp((7126.017*(-1)*0.000166666666666667)/(5.081527*0.93)).

FAQ

What is Cruise Weight Fraction for Prop-Driven Aircraft?

Cruise Weight Fraction for Prop-Driven Aircraft is a measure that estimates the proportion of an aircraft's weight during cruise, which is influenced by the range of the propeller aircraft, specific fuel consumption, maximum lift-to-drag ratio, and propeller efficiency, providing a crucial parameter in aircraft design and performance optimization and is represented as FW_{cruise prop} = exp((R_prop*(-1)*c)/(LDmax_ratio*η)) or Cruise Weight Fraction Propeller Aircraft = exp((Range of Propeller Aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*Propeller Efficiency)). Range of Propeller 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, The Maximum Lift-to-Drag Ratio is the highest ratio of lift force to drag force that an aircraft can achieve & Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).

How to calculate Cruise Weight Fraction for Prop-Driven Aircraft?

Cruise Weight Fraction for Prop-Driven Aircraft is a measure that estimates the proportion of an aircraft's weight during cruise, which is influenced by the range of the propeller aircraft, specific fuel consumption, maximum lift-to-drag ratio, and propeller efficiency, providing a crucial parameter in aircraft design and performance optimization is calculated using Cruise Weight Fraction Propeller Aircraft = exp((Range of Propeller Aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio*Propeller Efficiency)). To calculate Cruise Weight Fraction for Prop-Driven Aircraft, you need Range of Propeller Aircraft (R_prop), Specific Fuel Consumption (c), Maximum Lift-to-Drag Ratio (LDmax_ratio) & Propeller Efficiency (η). With our tool, you need to enter the respective value for Range of Propeller Aircraft, Specific Fuel Consumption, Maximum Lift-to-Drag Ratio & Propeller Efficiency and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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