Average Value Range Equation Calculator

✖Change in Weight refers to the difference in initial and the final weight.ⓘ Change in 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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Average Value Range Equation Solution

STEP 0: Pre-Calculation Summary

Formula Used

Average Value Range Equation = Change in 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.
Change in Weight - (Measured in Kilogram) - Change in Weight refers to the difference in initial and the final weight.
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

Change in Weight: 300 Kilogram --> 300 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: 114 Meter per Second --> 114 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R_AVG = Δw_f/(c_t*(F_D/V)) --> 300/(0.002825*(80/114))

Evaluating ... ...

R_AVG = 151327.433628319

STEP 3: Convert Result to Output's Unit

151327.433628319 Meter --> No Conversion Required

FINAL ANSWER

151327.433628319 ≈ 151327.4 Meter <-- Average Value Range Equation

(Calculation completed in 00.004 seconds)

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Credits

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

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< Jet Airplane Calculators

Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

LaTeX Go Thrust-Specific Fuel Consumption = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Endurance of Aircraft)

Endurance of Jet Airplane

LaTeX Go Endurance of Aircraft = Lift Coefficient*(ln(Gross Weight/Weight without Fuel))/(Drag Coefficient*Thrust-Specific Fuel Consumption)

Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag Ratio of Jet Airplane

LaTeX 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

LaTeX Go Endurance of Aircraft = (1/Thrust-Specific Fuel Consumption)*Lift-to-Drag Ratio*ln(Gross Weight/Weight without Fuel)

Average Value Range Equation Formula

LaTeX Go

Average Value Range Equation = Change in 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 = Change in Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity)) to calculate the Average Value Range Equation, The Average Value Range Equation calculates the average value of the aircraft range, this formula determines the average value based on the change in weight, the thrust-specific fuel consumption at the end of the range, the drag force at the end of the range, and the flight velocity at the end of the range. 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 Change in 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 -> 151327.4 = 300/(0.002825*(80/114)).

FAQ

What is Average Value Range Equation?

The Average Value Range Equation calculates the average value of the aircraft range, this formula determines the average value based on the change in weight, the thrust-specific fuel consumption at the end of the range, the drag force at the end of the range, and the flight velocity at the end of the range and is represented as R_AVG = Δw_f/(c_t*(F_D/V)) or Average Value Range Equation = Change in Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity)). Change in Weight refers to the difference in initial and the final weight, 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 calculates the average value of the aircraft range, this formula determines the average value based on the change in weight, the thrust-specific fuel consumption at the end of the range, the drag force at the end of the range, and the flight velocity at the end of the range is calculated using Average Value Range Equation = Change in Weight/(Thrust-Specific Fuel Consumption*(Drag Force/Flight Velocity)). To calculate Average Value Range Equation, you need Change in 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 Change in 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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