Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Parasite Drag Coefficient at zero lift
Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO
Thrust required for level, unaccelerated flight
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Dynamic pressure
Dynamic Pressure=Drag Force/(Drag Coefficient*Area) GO
Drag for a level, unaccelerated flight at negligible thrust angle
Drag Force=Dynamic Pressure*Area*Drag Coefficient GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

2 Other formulas that calculate the same Output

Range of Propeller-Driven Airplane
Range of aircraft=(Propeller efficiency/Specific Fuel Consumption)*(lift coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel)) GO
Range of Propeller-Driven Airplane for given lift-to-drag ratio
Range of aircraft=(Propeller efficiency/Specific Fuel Consumption)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel)) GO

Range of Jet Airplane Formula

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)))
R=(sqrt(8/(ρ<sub>∞</sub>*S)))*(1/(c<sub>t</sub>*C<sub>D</sub>))*(sqrt(C<sub>L</sub>))*((sqrt(W<sub>0</sub>))-(sqrt(W<sub>1</sub>)))
More formulas
Endurance of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane GO
Endurance for given Lift-to-Drag ratio of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane GO
Lift-to-Drag ratio for given Endurance of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Range of Jet Airplane GO

What is the range of a jet fighter?

Powered by two Pratt & Whitney F119-PW-100 turbofan engines with two-dimensional thrust vectoring nozzles, a fighter can fly at a maximum altitude of 20,000m and across a maximum range of 2,963km.

How to Calculate Range of Jet Airplane?

Range of Jet Airplane calculator uses 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))) to calculate the Range of aircraft, The Range of Jet Airplane is a function of altitude, thrust-specific fuel consumption, reference area, aerodynamic coefficients of lift & drag, and fuel weight. Range of aircraft and is denoted by R symbol.

How to calculate Range of Jet Airplane using this online calculator? To use this online calculator for Range of Jet Airplane, enter Freestream density ), Reference Area (S), Thrust-Specific Fuel Consumption (ct), Drag Coefficient (CD), lift coefficient (CL), Gross Weight (W0) and Weight without fuel (W1) and hit the calculate button. Here is how the Range of Jet Airplane calculation can be explained with given input values -> 4.371E-5 = (sqrt(8/(1.225*5)))*(1/(3*100))*(sqrt(10))*((sqrt(5000))-(sqrt(4500))).

FAQ

What is Range of Jet Airplane?
The Range of Jet Airplane is a function of altitude, thrust-specific fuel consumption, reference area, aerodynamic coefficients of lift & drag, and fuel weight and is represented as R=(sqrt(8/(ρ*S)))*(1/(ct*CD))*(sqrt(CL))*((sqrt(W0))-(sqrt(W1))) or 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))). Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output, Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. , The Gross Weight of the airplane is the weight with full fuel and payload and Weight without fuel is the total weight of the airplane without fuel.
How to calculate Range of Jet Airplane?
The Range of Jet Airplane is a function of altitude, thrust-specific fuel consumption, reference area, aerodynamic coefficients of lift & drag, and fuel weight is calculated using 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))). To calculate Range of Jet Airplane, you need Freestream density ), Reference Area (S), Thrust-Specific Fuel Consumption (ct), Drag Coefficient (CD), lift coefficient (CL), Gross Weight (W0) and Weight without fuel (W1). With our tool, you need to enter the respective value for Freestream density, Reference Area, Thrust-Specific Fuel Consumption, Drag Coefficient, lift coefficient, Gross Weight and Weight without fuel 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 Range of aircraft?
In this formula, Range of aircraft uses Freestream density, Reference Area, Thrust-Specific Fuel Consumption, Drag Coefficient, lift coefficient, Gross Weight and Weight without fuel. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Range of aircraft=(Propeller efficiency/Specific Fuel Consumption)*(lift coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
  • Range of aircraft=(Propeller efficiency/Specific Fuel Consumption)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
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