Battery Weight Fraction Calculator

⤿

Aircraft Design

Aircraft Performance

Introduction and Governing Equations

Static Stability and Control

⤿

⤿

✖Range of Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of Aircraft [R]			+10% -10%
✖Battery Specific Energy Capacity is a measure of how much energy a battery contains in comparison to its weight, typically expressed in Joule/kilogram or watt-hour/kilogram.ⓘ Battery Specific Energy Capacity [E_battery]			+10% -10%
✖The Efficiency of an electric motor is defined as the ratio of usable shaft power to electric input power.ⓘ Efficiency [η]			+10% -10%
✖Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.ⓘ Maximum Lift to Drag ratio of Aircraft [LDmax_ratio]			+10% -10%

✖Battery Weight Fraction is the ratio between battery weight to gross weight. It is a dimensionless number.ⓘ Battery Weight Fraction [WBF]

⎘ Copy

👎

Formula

✖

Battery Weight Fraction

Formula

`"WBF" = ("R"/("E"_{"battery"}*3600*"η"*(1/"[g]")*"LDmax"_{"ratio"}))`

Example

`"0.054049"=("10km"/("21J/kg"*3600*"0.80"*(1/"[g]")*"30"))`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF PDF Image

Battery Weight Fraction Solution

STEP 0: Pre-Calculation Summary

Formula Used

Battery Weight Fraction = (Range of Aircraft/(Battery Specific Energy Capacity*3600*Efficiency*(1/[g])*Maximum Lift to Drag ratio of Aircraft))
WBF = (R/(E_battery*3600*η*(1/[g])*LDmax_ratio))
This formula uses 1 Constants, 5 Variables

Constants Used

[g] - Gravitational acceleration on Earth Value Taken As 9.80665

Variables Used

Battery Weight Fraction - Battery Weight Fraction is the ratio between battery weight to gross weight. It is a dimensionless number.
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.
Battery Specific Energy Capacity - (Measured in Joule per Kilogram) - Battery Specific Energy Capacity is a measure of how much energy a battery contains in comparison to its weight, typically expressed in Joule/kilogram or watt-hour/kilogram.
Efficiency - The Efficiency of an electric motor is defined as the ratio of usable shaft power to electric input power.
Maximum Lift to Drag ratio of Aircraft - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.

STEP 1: Convert Input(s) to Base Unit

Range of Aircraft: 10 Kilometer --> 10000 Meter (Check conversion here)
Battery Specific Energy Capacity: 21 Joule per Kilogram --> 21 Joule per Kilogram No Conversion Required
Efficiency: 0.8 --> No Conversion Required
Maximum Lift to Drag ratio of Aircraft: 30 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

WBF = (R/(E_battery*3600*η*(1/[g])*LDmax_ratio)) --> (10000/(21*3600*0.8*(1/[g])*30))

Evaluating ... ...

WBF = 0.0540489969135802

STEP 3: Convert Result to Output's Unit

0.0540489969135802 --> No Conversion Required

FINAL ANSWER

0.0540489969135802 ≈ 0.054049 <-- Battery Weight Fraction

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Design » Conceptual Design » Design Process » Battery Weight Fraction

Credits

Created by Prasana Kannan

Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai

Prasana Kannan has created this Calculator and 25+ more calculators!

Verified by Kaki Varun Krishna

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad

Kaki Varun Krishna has verified this Calculator and 10+ more calculators!

< 19 Design Process Calculators

Summations of priorities of objectives that need to be maximized (Millitary planes)

Go Priority Sum of objectives to be maximized (%) = Performance Priority (%)+Flight Quality Priority (%)+Scariness Priority (%)+Maintainability Priority (%)+Producibility Priority (%)+Disposability Priority (%)+Stealth Priority (%)

Thrust-to-Weight ratio given vertical velocity

Go Thrust-to-weight ratio = ((Vertical Airspeed/Aircraft Velocity)+((Dynamic Pressure/Wing Loading)*(Minimum Drag Coefficient))+((Lift Induced Drag Constant/Dynamic Pressure)*(Wing Loading)))

Priority of objective weight in design process given minimum design index

Go Weight Priority (%) = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Index

Priority of objective cost in design process given minimum design index

Go Cost Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Index

Priority of objective period of design given minimum design index

Go Period Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Index

Period of Design Index given Minimum Design Index

Go Period Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Priority (%)

Weight Index given Minimum Design Index

Go Weight Index = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Priority (%)

Cost Index given Minimum Design Index

Go Cost Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Priority (%)

Minimum design index

Go Minimum Design Index = ((Cost Index*Cost Priority (%))+(Weight Index*Weight Priority (%))+(Period Index*Period Priority (%)))/100

Battery Weight Fraction

Go Battery Weight Fraction = (Range of Aircraft/(Battery Specific Energy Capacity*3600*Efficiency*(1/[g])*Maximum Lift to Drag ratio of Aircraft))

Summation of priorities of all objectives that need to be minimized

Go Priority Sum of objectives to be minimized(%) = Cost Priority (%)+Weight Priority (%)+Period Priority (%)

Electric Power for Wind Turbine

Go Electric Power of Wind Turbine = Shaft Power*Efficiency of Generator*Efficiency of Transmission

Propulsion Net Thrust

Go Thrust force = Air Mass Flow Rate*(Velocity of Jet-Flight Velocity)

Maximum payload capability

Go Payload = Maximum take off weight-Operating empty weight-Fuel load

Induced Inflow Ratio in Hover

Go Inflow Ratio = Induced Velocity/(Rotor Radius*Angular Velocity)

Range increment of aircraft

Go Range increment of aircraft = Design range-Harmonic range

Mission fuel

Go Mission fuel = Fuel load-Reserve fuel

Reserve fuel

Go Reserve fuel = Fuel load-Mission fuel

Fuel load

Go Fuel load = Mission fuel+Reserve fuel

Battery Weight Fraction Formula

Battery Weight Fraction = (Range of Aircraft/(Battery Specific Energy Capacity*3600*Efficiency*(1/[g])*Maximum Lift to Drag ratio of Aircraft))
WBF = (R/(E_battery*3600*η*(1/[g])*LDmax_ratio))

What is maximum lift over drag ratio?

Maximum lift over drag value affects directly and mainly the fuel and battery weight estimation. It's given by (L/D)max.

How to Calculate Battery Weight Fraction?

Battery Weight Fraction calculator uses Battery Weight Fraction = (Range of Aircraft/(Battery Specific Energy Capacity*3600*Efficiency*(1/[g])*Maximum Lift to Drag ratio of Aircraft)) to calculate the Battery Weight Fraction, The Battery Weight Fraction refers to the proportion of the aircraft's total weight that is attributed to the battery or batteries onboard. It is expressed as a fraction or percentage of the aircraft's total weight. Battery Weight Fraction is denoted by WBF symbol.

How to calculate Battery Weight Fraction using this online calculator? To use this online calculator for Battery Weight Fraction, enter Range of Aircraft (R), Battery Specific Energy Capacity (E_battery), Efficiency (η) & Maximum Lift to Drag ratio of Aircraft (LDmax_ratio) and hit the calculate button. Here is how the Battery Weight Fraction calculation can be explained with given input values -> 0.054049 = (10000/(21*3600*0.8*(1/[g])*30)).

FAQ

What is Battery Weight Fraction?

The Battery Weight Fraction refers to the proportion of the aircraft's total weight that is attributed to the battery or batteries onboard. It is expressed as a fraction or percentage of the aircraft's total weight and is represented as WBF = (R/(E_battery*3600*η*(1/[g])*LDmax_ratio)) or Battery Weight Fraction = (Range of Aircraft/(Battery Specific Energy Capacity*3600*Efficiency*(1/[g])*Maximum Lift to Drag ratio of Aircraft)). Range of Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, Battery Specific Energy Capacity is a measure of how much energy a battery contains in comparison to its weight, typically expressed in Joule/kilogram or watt-hour/kilogram, The Efficiency of an electric motor is defined as the ratio of usable shaft power to electric input power & Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.

How to calculate Battery Weight Fraction?

The Battery Weight Fraction refers to the proportion of the aircraft's total weight that is attributed to the battery or batteries onboard. It is expressed as a fraction or percentage of the aircraft's total weight is calculated using Battery Weight Fraction = (Range of Aircraft/(Battery Specific Energy Capacity*3600*Efficiency*(1/[g])*Maximum Lift to Drag ratio of Aircraft)). To calculate Battery Weight Fraction, you need Range of Aircraft (R), Battery Specific Energy Capacity (E_battery), Efficiency (η) & Maximum Lift to Drag ratio of Aircraft (LDmax_ratio). With our tool, you need to enter the respective value for Range of Aircraft, Battery Specific Energy Capacity, Efficiency & Maximum Lift to Drag ratio of Aircraft and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search