## Credits

Created by Saurabh Patil
Shri Govindram Seksaria Institute of Technology and Science (SGSITS ), Indore
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## Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary
Formula Used
Maximum Lift to Drag ratio of Aircraft = Lift to Drag ratio at maximum Endurance/0.866
L/Dmax = L/D(Emax)/0.866
This formula uses 1 Variables
Variables Used
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.
STEP 1: Convert Input(s) to Base Unit
Lift to Drag ratio at maximum Endurance: 20 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
L/Dmax = L/D(Emax)/0.866 --> 20/0.866
Evaluating ... ...
L/Dmax = 23.094688221709
STEP 3: Convert Result to Output's Unit
23.094688221709 --> No Conversion Required
23.094688221709 <-- Maximum Lift to Drag ratio of Aircraft
(Calculation completed in 00.000 seconds)

## < 10+ Aircraft Preliminary Weight Built Up Calculators

Optimum Range for Jet Aircraft in Cruising Phase
Range of aircraft = ((Velocity at maximum lift to drag ratio*Maximum Lift to Drag ratio of Aircraft)/Specific Fuel Consumption)*ln(Weight of aircraft at beginning of Cruise phase/Weight of aircraft at end of Cruise phase) Go
Optimum Range for Prop-Driven Aircraft in Cruising Phase
Range of aircraft = ((Propeller efficiency*Maximum Lift to Drag ratio of Aircraft)/Specific Fuel Consumption)*ln(Weight of aircraft at beginning of Cruise phase/Weight of aircraft at end of Cruise phase) Go
Cruise Weight Fraction for Jet Aircraft
Cruise Weight Fraction = exp((Range of aircraft*Specific Fuel Consumption*(-1))/(0.866*1.32*Velocity at maximum lift to drag ratio*Maximum Lift to Drag ratio of Aircraft)) Go
Cruise Weight Fraction for Prop-Driven Aircraft
Cruise Weight Fraction = exp((Range of aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift to Drag ratio of Aircraft*Propeller efficiency)) Go
Preliminary Take Off Weight Built-up for manned aircraft
Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight Go
Payload Weight in terms of Takeoff Weight
Payload Carried = Desired Takeoff Weight-Operating Empty Weight-Crew Weight-Fuel Weight to be Carried Go
Crew Weight in terms of Takeoff Weight
Crew Weight = Desired Takeoff Weight-Payload Carried-Fuel Weight to be Carried-Operating Empty Weight Go
Preliminary Take off Weight Built-up for manned aircraft in terms of fuel and empty weight fraction
Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction) Go
Empty Weight Fraction
Empty Weight Fraction = Operating Empty Weight/Desired Takeoff Weight Go
Fuel Fraction
Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight Go

### Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft Formula

Maximum Lift to Drag ratio of Aircraft = Lift to Drag ratio at maximum Endurance/0.866
L/Dmax = L/D(Emax)/0.866

## 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 Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft?

Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft calculator uses Maximum Lift to Drag ratio of Aircraft = Lift to Drag ratio at maximum Endurance/0.866 to calculate the Maximum Lift to Drag ratio of Aircraft, Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft is the maximum lift to drag ratio that a plane can achieve, theoretically, it's ~115.5% of lift to drag ratio at maximum endurance. Maximum Lift to Drag ratio of Aircraft is denoted by L/Dmax symbol.

How to calculate Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft using this online calculator? To use this online calculator for Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft, enter Lift to Drag ratio at maximum Endurance (L/D(Emax)) and hit the calculate button. Here is how the Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft calculation can be explained with given input values -> 23.09469 = 20/0.866.

### FAQ

What is Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft?
Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft is the maximum lift to drag ratio that a plane can achieve, theoretically, it's ~115.5% of lift to drag ratio at maximum endurance and is represented as L/Dmax = L/D(Emax)/0.866 or Maximum Lift to Drag ratio of Aircraft = Lift to Drag ratio at maximum Endurance/0.866. 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.
How to calculate Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft?
Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft is the maximum lift to drag ratio that a plane can achieve, theoretically, it's ~115.5% of lift to drag ratio at maximum endurance is calculated using Maximum Lift to Drag ratio of Aircraft = Lift to Drag ratio at maximum Endurance/0.866. To calculate Maximum Lift to Drag Ratio in terms of Lift to Drag Ratio for max endurance of Prop-Driven Aircraft, you need Lift to Drag ratio at maximum Endurance (L/D(Emax)). With our tool, you need to enter the respective value for Lift to Drag ratio at maximum Endurance 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 Maximum Lift to Drag ratio of Aircraft?
In this formula, Maximum Lift to Drag ratio of Aircraft uses Lift to Drag ratio at maximum Endurance. We can use 4 other way(s) to calculate the same, which is/are as follows -
• Maximum Lift to Drag ratio of Aircraft = (Range of aircraft*Specific Fuel Consumption)/(Velocity at maximum lift to drag ratio*ln(Weight of aircraft at beginning of Cruise phase/Weight of aircraft at end of Cruise phase))
• Maximum Lift to Drag ratio of Aircraft = (Range of aircraft*Specific Fuel Consumption)/(Propeller efficiency*ln(Weight of aircraft at beginning of Cruise phase/Weight of aircraft at end of Cruise phase))
• Maximum Lift to Drag ratio of Aircraft = (Endurance of aircraft*Specific Fuel Consumption)/ln(Weight of aircraft at beginning of Loiter phase/Weight of aircraft at end of Loiter phase)
• Maximum Lift to Drag ratio of Aircraft = Landing Mass Fraction* (((Aspect Ratio of a wing)/ (Aircraft wetted area/Reference Area))^(0.5))
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