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Preliminary Endurance for Prop-Driven Aircraft Calculator

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Preliminary Design Conceptual Design

✖Lift to Drag Ratio at Maximum Endurance is the ratio of lift to drag at which the plane can fly (or Loiter) for maximum time.ⓘ Lift to Drag Ratio at Maximum Endurance [LDEmax_ratio]			+10% -10%
✖Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).ⓘ Propeller Efficiency [η]			+10% -10%
✖Weight of Aircraft at Beginning of Loiter Phase is considered as the weight of the plane just before going to loiter phase.ⓘ Weight of Aircraft at Beginning of Loiter Phase [W_L(beg)]			+10% -10%
✖Weight of Aircraft at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered.ⓘ Weight of Aircraft at End of Loiter Phase [W_L,end]			+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%
✖Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.ⓘ Velocity for Maximum Endurance [V_(Emax)]			+10% -10%

✖Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Preliminary Endurance for Prop-Driven Aircraft [E]

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Preliminary Endurance for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance)
E = (LDEmax_ratio*η*ln(W_L(beg)/W_L,end))/(c*V_(Emax))
This formula uses 1 Functions, 7 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

Endurance of Aircraft - (Measured in Second) - Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.
Lift to Drag Ratio at Maximum Endurance - Lift to Drag Ratio at Maximum Endurance is the ratio of lift to drag at which the plane can fly (or Loiter) for maximum time.
Propeller Efficiency - Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power).
Weight of Aircraft at Beginning of Loiter Phase - (Measured in Kilogram) - Weight of Aircraft at Beginning of Loiter Phase is considered as the weight of the plane just before going to loiter phase.
Weight of Aircraft at End of Loiter Phase - (Measured in Kilogram) - Weight of Aircraft at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered.
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.
Velocity for Maximum Endurance - (Measured in Meter per Second) - Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.

STEP 1: Convert Input(s) to Base Unit

Lift to Drag Ratio at Maximum Endurance: 26 --> No Conversion Required
Propeller Efficiency: 0.93 --> No Conversion Required
Weight of Aircraft at Beginning of Loiter Phase: 400 Kilogram --> 400 Kilogram No Conversion Required
Weight of Aircraft at End of Loiter Phase: 300 Kilogram --> 300 Kilogram No Conversion Required
Power Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Velocity for Maximum Endurance: 40 Knot --> 20.5777777777778 Meter per Second (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

E = (LDEmax_ratio*η*ln(W_L(beg)/W_L,end))/(c*V_(Emax)) --> (26*0.93*ln(400/300))/(0.000166666666666667*20.5777777777778)

Evaluating ... ...

E = 2028.2518123204

STEP 3: Convert Result to Output's Unit

2028.2518123204 Second --> No Conversion Required

FINAL ANSWER

2028.2518123204 ≈ 2028.252 Second <-- Endurance of Aircraft

(Calculation completed in 00.020 seconds)

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Created by Vedant Chitte

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

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< 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

Preliminary Endurance for Prop-Driven Aircraft Formula

LaTeX Go

What do you mean by Endurance of Aircraft?

In aviation, endurance is the maximum length of time that an aircraft can spend in a cruising flight. In other words, it is the amount of time an aircraft can stay in the air with one load of fuel. Endurance is different from range, which is a measure of distance flown. For example, a typical sailplane exhibits high endurance characteristics but poor range characteristics. Endurance can factor into aviation design in a number of ways. Some aircraft, require high endurance characteristics as part of their mission profile (often referred to as loiter time). Endurance plays a prime factor in finding out the fuel fraction for an aircraft. Endurance, like range, is also related to fuel efficiency; fuel-efficient aircraft will tend to exhibit good endurance characteristics.

How to Calculate Preliminary Endurance for Prop-Driven Aircraft?

Preliminary Endurance for Prop-Driven Aircraft calculator uses Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance) to calculate the Endurance of Aircraft, The Preliminary endurance for Prop-Driven Aircraft formula provides an estimate of the maximum amount of time the propeller-driven aircraft can remain in flight on a single fuel load under normal operating conditions, this formula calculates the endurance of the aircraft by multiplying various factors related to aerodynamic efficiency, propeller efficiency, weight change during flight, and engine fuel consumption characteristics. Endurance of Aircraft is denoted by E symbol.

How to calculate Preliminary Endurance for Prop-Driven Aircraft using this online calculator? To use this online calculator for Preliminary Endurance for Prop-Driven Aircraft, enter Lift to Drag Ratio at Maximum Endurance (LDEmax_ratio), Propeller Efficiency (η), Weight of Aircraft at Beginning of Loiter Phase (W_L(beg)), Weight of Aircraft at End of Loiter Phase (W_L,end), Power Specific Fuel Consumption (c) & Velocity for Maximum Endurance (V_(Emax)) and hit the calculate button. Here is how the Preliminary Endurance for Prop-Driven Aircraft calculation can be explained with given input values -> 2028.252 = (26*0.93*ln(400/300))/(0.000166666666666667*20.5777777777778).

FAQ

What is Preliminary Endurance for Prop-Driven Aircraft?

The Preliminary endurance for Prop-Driven Aircraft formula provides an estimate of the maximum amount of time the propeller-driven aircraft can remain in flight on a single fuel load under normal operating conditions, this formula calculates the endurance of the aircraft by multiplying various factors related to aerodynamic efficiency, propeller efficiency, weight change during flight, and engine fuel consumption characteristics and is represented as E = (LDEmax_ratio*η*ln(W_L(beg)/W_L,end))/(c*V_(Emax)) or Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance). Lift to Drag Ratio at Maximum Endurance is the ratio of lift to drag at which the plane can fly (or Loiter) for maximum time, Propeller Efficiency is defined as power produced (propeller power) divided by power applied (engine power), Weight of Aircraft at Beginning of Loiter Phase is considered as the weight of the plane just before going to loiter phase, Weight of Aircraft at End of Loiter Phase is considered for the Preliminary Endurance Calculation. For the calculation of preliminary endurance, the loiter phase is considered, Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time & Velocity for Maximum Endurance is velocity of plane at which a plane can loiter for maximum time i.e. for maximum endurance.

How to calculate Preliminary Endurance for Prop-Driven Aircraft?

The Preliminary endurance for Prop-Driven Aircraft formula provides an estimate of the maximum amount of time the propeller-driven aircraft can remain in flight on a single fuel load under normal operating conditions, this formula calculates the endurance of the aircraft by multiplying various factors related to aerodynamic efficiency, propeller efficiency, weight change during flight, and engine fuel consumption characteristics is calculated using Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance). To calculate Preliminary Endurance for Prop-Driven Aircraft, you need Lift to Drag Ratio at Maximum Endurance (LDEmax_ratio), Propeller Efficiency (η), Weight of Aircraft at Beginning of Loiter Phase (W_L(beg)), Weight of Aircraft at End of Loiter Phase (W_L,end), Power Specific Fuel Consumption (c) & Velocity for Maximum Endurance (V_(Emax)). With our tool, you need to enter the respective value for Lift to Drag Ratio at Maximum Endurance, Propeller Efficiency, Weight of Aircraft at Beginning of Loiter Phase, Weight of Aircraft at End of Loiter Phase, Power Specific Fuel Consumption & Velocity for Maximum Endurance 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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