LCM of two numbers

Optimum Range for Jet Aircraft in Cruising Phase Calculator

Physics Chemistry Engineering Financial More >>

↳

Aerospace Basic Physics Mechanical Others and Extra

⤿

Aircraft Mechanics Aerodynamics Orbital Mechanics Propulsion

⤿

Aircraft Design Aircraft Performance Introduction and Governing Equations Static Stability and Control

⤿

Preliminary Design Conceptual Design

✖Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.ⓘ Velocity at Maximum Lift to Drag Ratio [V_L/D(max)]			+10% -10%
✖Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.ⓘ Maximum Lift-to-Drag Ratio of Aircraft [LDmax_ratio]			+10% -10%
✖Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Power Specific Fuel Consumption [c]			+10% -10%
✖Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.ⓘ Weight of Aircraft at Beginning of Cruise Phase [W_i]			+10% -10%
✖Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.ⓘ Weight of Aircraft at End of Cruise Phase [W_f]			+10% -10%

✖Range of Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Optimum Range for Jet Aircraft in Cruising Phase [R]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Preliminary Design Formulas PDF PDF Image

Optimum Range for Jet Aircraft in Cruising Phase Solution

STEP 0: Pre-Calculation Summary

Formula Used

Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)
R = (V_L/D(max)*LDmax_ratio)/c*ln(W_i/W_f)
This formula uses 1 Functions, 6 Variables

Functions Used

ln - The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function., ln(Number)

Variables Used

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.
Velocity at Maximum Lift to Drag Ratio - (Measured in Meter per Second) - Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.
Maximum Lift-to-Drag Ratio of Aircraft - Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.
Power Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
Weight of Aircraft at Beginning of Cruise Phase - (Measured in Kilogram) - Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.
Weight of Aircraft at End of Cruise Phase - (Measured in Kilogram) - Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

STEP 1: Convert Input(s) to Base Unit

Velocity at Maximum Lift to Drag Ratio: 42.9 Knot --> 22.0696666666667 Meter per Second (Check conversion here)
Maximum Lift-to-Drag Ratio of Aircraft: 19.7 --> No Conversion Required
Power Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Weight of Aircraft at Beginning of Cruise Phase: 514 Kilogram --> 514 Kilogram No Conversion Required
Weight of Aircraft at End of Cruise Phase: 350 Kilogram --> 350 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R = (V_L/D(max)*LDmax_ratio)/c*ln(W_i/W_f) --> (22.0696666666667*19.7)/0.000166666666666667*ln(514/350)

Evaluating ... ...

R = 1002472.47991863

STEP 3: Convert Result to Output's Unit

1002472.47991863 Meter -->1002.47247991863 Kilometer (Check conversion here)

FINAL ANSWER

1002.47247991863 ≈ 1002.472 Kilometer <-- Range of Aircraft

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Design » Aerospace » Preliminary Design » Optimum Range for Jet Aircraft in Cruising Phase

Credits

Created by Vedant Chitte

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

Vedant Chitte has created this Calculator and 25+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< Preliminary Design Calculators

Optimum Range for Jet Aircraft in Cruising Phase

LaTeX Go Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)

Preliminary Take Off Weight Built-up for Manned Aircraft

LaTeX Go Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight

Preliminary Take off Weight Built-Up for Manned Aircraft given Fuel and Empty Weight Fraction

LaTeX Go Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction)

Fuel Fraction

LaTeX Go Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight

Optimum Range for Jet Aircraft in Cruising Phase Formula

LaTeX Go

What is Range of Aircraft?

The maximal total range is the maximum distance an aircraft can fly between takeoff and landing, as limited by fuel capacity in powered aircraft, or cross-country speed and environmental conditions in unpowered aircraft. The range can be seen as the cross-country ground speed multiplied by the maximum time in the air. The fuel time limit for powered aircraft is fixed by the fuel load and rate of consumption. When all fuel is consumed, the engines stop and the aircraft will lose its propulsion.

How to Calculate Optimum Range for Jet Aircraft in Cruising Phase?

Optimum Range for Jet Aircraft in Cruising Phase calculator uses Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase) to calculate the Range of Aircraft, The Optimum Range for Jet Aircraft in Cruising Phase formula gives you the maximum distance the aircraft can travel while optimizing fuel efficiency during the cruising phase, the optimum range for a jet aircraft during the cruising phase refers to the maximum distance the aircraft can travel while minimizing fuel consumption, achieving optimum range involves optimizing various factors such as airspeed, altitude, engine settings, and flight profile to minimize drag and maximize fuel efficiency. Range of Aircraft is denoted by R symbol.

How to calculate Optimum Range for Jet Aircraft in Cruising Phase using this online calculator? To use this online calculator for Optimum Range for Jet Aircraft in Cruising Phase, enter Velocity at Maximum Lift to Drag Ratio (V_L/D(max)), Maximum Lift-to-Drag Ratio of Aircraft (LDmax_ratio), Power Specific Fuel Consumption (c), Weight of Aircraft at Beginning of Cruise Phase (W_i) & Weight of Aircraft at End of Cruise Phase (W_f) and hit the calculate button. Here is how the Optimum Range for Jet Aircraft in Cruising Phase calculation can be explained with given input values -> 0.997392 = (22.0696666666667*19.7)/0.000166666666666667*ln(514/350).

FAQ

What is Optimum Range for Jet Aircraft in Cruising Phase?

The Optimum Range for Jet Aircraft in Cruising Phase formula gives you the maximum distance the aircraft can travel while optimizing fuel efficiency during the cruising phase, the optimum range for a jet aircraft during the cruising phase refers to the maximum distance the aircraft can travel while minimizing fuel consumption, achieving optimum range involves optimizing various factors such as airspeed, altitude, engine settings, and flight profile to minimize drag and maximize fuel efficiency and is represented as R = (V_L/D(max)*LDmax_ratio)/c*ln(W_i/W_f) or Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase). Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase, Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight, Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission & Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

How to calculate Optimum Range for Jet Aircraft in Cruising Phase?

The Optimum Range for Jet Aircraft in Cruising Phase formula gives you the maximum distance the aircraft can travel while optimizing fuel efficiency during the cruising phase, the optimum range for a jet aircraft during the cruising phase refers to the maximum distance the aircraft can travel while minimizing fuel consumption, achieving optimum range involves optimizing various factors such as airspeed, altitude, engine settings, and flight profile to minimize drag and maximize fuel efficiency is calculated using Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase). To calculate Optimum Range for Jet Aircraft in Cruising Phase, you need Velocity at Maximum Lift to Drag Ratio (V_L/D(max)), Maximum Lift-to-Drag Ratio of Aircraft (LDmax_ratio), Power Specific Fuel Consumption (c), Weight of Aircraft at Beginning of Cruise Phase (W_i) & Weight of Aircraft at End of Cruise Phase (W_f). With our tool, you need to enter the respective value for Velocity at Maximum Lift to Drag Ratio, Maximum Lift-to-Drag Ratio of Aircraft, Power Specific Fuel Consumption, Weight of Aircraft at Beginning of Cruise Phase & Weight of Aircraft at End of Cruise Phase 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 Velocity at Maximum Lift to Drag Ratio, Maximum Lift-to-Drag Ratio of Aircraft, Power Specific Fuel Consumption, Weight of Aircraft at Beginning of Cruise Phase & Weight of Aircraft at End of Cruise Phase. We can use 1 other way(s) to calculate the same, which is/are as follows -

Range of Aircraft = 270*Weight of Fuel/Aircraft Weight*Lift Coefficient/Drag Coefficient*Rotor Efficiency*(Coefficient of Power loss)/Power Specific Fuel Consumption

Home

FREE PDFs

🔍 Search