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Velocity at Maximum Endurance given 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%
✖Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.ⓘ Endurance of Aircraft [E]			+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 at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft [V_(Emax)]

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Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Velocity for Maximum Endurance = (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*Endurance of Aircraft)
V_(Emax) = (LDEmax_ratio*η*ln(W_L(beg)/W_L,end))/(c*E)
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

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.
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.
Endurance of Aircraft - (Measured in Second) - Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.

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)
Endurance of Aircraft: 2028 Second --> 2028 Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_(Emax) = (LDEmax_ratio*η*ln(W_L(beg)/W_L,end))/(c*E) --> (26*0.93*ln(400/300))/(0.000166666666666667*2028)

Evaluating ... ...

V_(Emax) = 20.5803328753966

STEP 3: Convert Result to Output's Unit

20.5803328753966 Meter per Second -->40.0049667124339 Knot (Check conversion here)

FINAL ANSWER

40.0049667124339 ≈ 40.00497 Knot <-- Velocity for Maximum Endurance

(Calculation completed in 00.008 seconds)

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Shri Govindram Seksaria Institute of Technology and Science (SGSITS ), Indore

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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

Velocity at Maximum Endurance given 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 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 Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft calculator uses Velocity for Maximum Endurance = (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*Endurance of Aircraft) to calculate the Velocity for Maximum Endurance, The Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft formula calculation gives you the velocity at which the aircraft achieves its maximum endurance, allowing for efficient flight planning and optimization of fuel consumption during endurance missions. Velocity for Maximum Endurance is denoted by V_(Emax) symbol.

How to calculate Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft using this online calculator? To use this online calculator for Velocity at Maximum Endurance given 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) & Endurance of Aircraft (E) and hit the calculate button. Here is how the Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft calculation can be explained with given input values -> 78.85212 = (26*0.93*ln(400/300))/(0.000166666666666667*2028).

FAQ

What is Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

The Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft formula calculation gives you the velocity at which the aircraft achieves its maximum endurance, allowing for efficient flight planning and optimization of fuel consumption during endurance missions and is represented as V_(Emax) = (LDEmax_ratio*η*ln(W_L(beg)/W_L,end))/(c*E) or Velocity for Maximum Endurance = (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*Endurance of Aircraft). 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 & Endurance of Aircraft is the maximum length of time that an aircraft can spend in cruising flight.

How to calculate Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft?

The Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft formula calculation gives you the velocity at which the aircraft achieves its maximum endurance, allowing for efficient flight planning and optimization of fuel consumption during endurance missions is calculated using Velocity for Maximum Endurance = (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*Endurance of Aircraft). To calculate Velocity at Maximum Endurance given 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) & Endurance of Aircraft (E). 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 & Endurance of Aircraft 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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