Average Value Range Equation Calculator

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Aircraft Performance

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Propeller-Driven Airplane

✖weight refers to the force exerted on an object due to gravity. It is the product of an object's mass and the acceleration due to gravity.ⓘ Weight [Δw_f]			+10% -10%
✖Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output.ⓘ Thrust-Specific Fuel Consumption [c_t]			+10% -10%
✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag Force [F_D]			+10% -10%
✖Flight Velocity is the speed with which the aircraft moves through the air.ⓘ Flight Velocity [V]			+10% -10%

✖The Average value range equation is to estimate an aircraft’s range. Range is simply aircraft velocity times endurance.ⓘ Average Value Range Equation [R_AVG]

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Formula

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Average Value Range Equation

Formula

`"R"_{"AVG"} = "Δw"_{"f"}/("c"_{"t"}*("F"_{"D"}/"V"))`

Example

`"7964.602m"="30kg"/("10.17kg/h/N"*("80N"/"60m/s"))`

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Average Value Range Equation Solution

STEP 0: Pre-Calculation Summary

Formula Used

Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity))
R_AVG = Δw_f/(c_t*(F_D/V))
This formula uses 5 Variables

Variables Used

Average Value Range Equation - (Measured in Meter) - The Average value range equation is to estimate an aircraft’s range. Range is simply aircraft velocity times endurance.
Weight - (Measured in Kilogram) - weight refers to the force exerted on an object due to gravity. It is the product of an object's mass and the acceleration due to gravity.
Thrust-Specific Fuel Consumption - (Measured in Kilogram per Second per Newton) - Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Flight Velocity - (Measured in Meter per Second) - Flight Velocity is the speed with which the aircraft moves through the air.

STEP 1: Convert Input(s) to Base Unit

Weight: 30 Kilogram --> 30 Kilogram No Conversion Required
Thrust-Specific Fuel Consumption: 10.17 Kilogram per Hour per Newton --> 0.002825 Kilogram per Second per Newton (Check conversion here)
Drag Force: 80 Newton --> 80 Newton No Conversion Required
Flight Velocity: 60 Meter per Second --> 60 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R_AVG = Δw_f/(c_t*(F_D/V)) --> 30/(0.002825*(80/60))

Evaluating ... ...

R_AVG = 7964.6017699115

STEP 3: Convert Result to Output's Unit

7964.6017699115 Meter --> No Conversion Required

FINAL ANSWER

7964.6017699115 ≈ 7964.602 Meter <-- Average Value Range Equation

(Calculation completed in 00.007 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Range and Endurance » Jet Airplane » Average Value Range Equation

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Created by Sastika Ilango

Sri Ramakrishna Engineering College (SREC), COIMBATORE

Sastika Ilango has created this Calculator and 9 more calculators!

Verified by Harsh Raj

Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

Harsh Raj has verified this Calculator and 25+ more calculators!

< 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))

Average Value Range Equation Formula

Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity))
R_AVG = Δw_f/(c_t*(F_D/V))

What is Average Value Range Equation ?

An average value equation to estimate an aircraft’s range. Range is simply aircraft velocity
times endurance.

How to Calculate Average Value Range Equation?

Average Value Range Equation calculator uses Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity)) to calculate the Average Value Range Equation, The Average Value Range Equation formula is defined as the overall aerodynamic efficiency of the entire flight profile. Average Value Range Equation is denoted by R_AVG symbol.

How to calculate Average Value Range Equation using this online calculator? To use this online calculator for Average Value Range Equation, enter Weight (Δw_f), Thrust-Specific Fuel Consumption (c_t), Drag Force (F_D) & Flight Velocity (V) and hit the calculate button. Here is how the Average Value Range Equation calculation can be explained with given input values -> 27000 = 30/(0.002825*(80/60)).

FAQ

What is Average Value Range Equation?

The Average Value Range Equation formula is defined as the overall aerodynamic efficiency of the entire flight profile and is represented as R_AVG = Δw_f/(c_t*(F_D/V)) or Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity)). weight refers to the force exerted on an object due to gravity. It is the product of an object's mass and the acceleration due to gravity, Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output, Drag Force is the resisting force experienced by an object moving through a fluid & Flight Velocity is the speed with which the aircraft moves through the air.

How to calculate Average Value Range Equation?

The Average Value Range Equation formula is defined as the overall aerodynamic efficiency of the entire flight profile is calculated using Average Value Range Equation = Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity)). To calculate Average Value Range Equation, you need Weight (Δw_f), Thrust-Specific Fuel Consumption (c_t), Drag Force (F_D) & Flight Velocity (V). With our tool, you need to enter the respective value for Weight, Thrust-Specific Fuel Consumption, Drag Force & Flight Velocity 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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