Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft Solution

STEP 0: Pre-Calculation Summary
Formula Used
Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866
LDmaxratio = LDEmaxratio/0.866
This formula uses 2 Variables
Variables Used
Maximum Lift to Drag Ratio - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
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: 4.4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
LDmaxratio = LDEmaxratio/0.866 --> 4.4/0.866
Evaluating ... ...
LDmaxratio = 5.08083140877598
STEP 3: Convert Result to Output's Unit
5.08083140877598 --> No Conversion Required
FINAL ANSWER
5.08083140877598 5.080831 <-- Maximum Lift to Drag Ratio
(Calculation completed in 00.004 seconds)

Credits

Created by Saurabh Patil
Shri Govindram Seksaria Institute of Technology and Science (SGSITS ), Indore
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21 Propeller-Driven Airplane Calculators

Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Go Propeller Efficiency = Endurance of Aircraft/((1/Specific Fuel Consumption)*((Lift Coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Weight without fuel)^(1/2))-((1/Gross Weight)^(1/2))))
Endurance of Propeller-Driven Airplane
Go Endurance of Aircraft = Propeller Efficiency/Specific Fuel Consumption*(Lift Coefficient^1.5)/Drag Coefficient*sqrt(2*Freestream density*Reference Area)*((1/Weight without fuel)^(1/2)-(1/Gross Weight)^(1/2))
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Go Specific Fuel Consumption = Propeller Efficiency/Endurance of Aircraft*Lift Coefficient^1.5/Drag Coefficient*sqrt(2*Freestream density*Reference Area)*((1/Weight without fuel)^(1/2)-(1/Gross Weight)^(1/2))
Lift to Drag for Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft
Go Lift to Drag Ratio at Maximum Endurance = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))
Specific Fuel Consumption given Preliminary Endurance for Prop-Driven Aircraft
Go Specific Fuel Consumption = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))/(Endurance of Aircraft*Velocity for Maximum Endurance)
Propeller Efficiency given Preliminary Endurance for Prop-Driven Aircraft
Go Propeller Efficiency = (Endurance of Aircraft*Velocity for Maximum Endurance*Specific Fuel Consumption)/(Lift to Drag Ratio at Maximum Endurance*ln(Weight at Start of Loiter Phase/Weight at End of Loiter Phase))
Specific Fuel Consumption for given Range of Propeller-Driven Airplane
Go Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
Range of Propeller-Driven Airplane
Go Range of aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift Coefficient/Drag Coefficient)*(ln(Gross Weight/Weight without fuel))
Propeller Efficiency for given Range of Propeller-Driven Airplane
Go Propeller Efficiency = Range of aircraft*Specific Fuel Consumption*Drag Coefficient/(Lift Coefficient*ln(Gross Weight/Weight without fuel))
Maximum Lift to Drag Ratio given Range for Prop-driven Aircraft
Go Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
Propeller Efficiency given Range for Prop-Driven Aircraft
Go Propeller Efficiency = (Range of aircraft*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
Specific Fuel Consumption given Range for Prop-Driven Aircraft
Go Specific Fuel Consumption = (Propeller Efficiency*Maximum Lift to Drag Ratio*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))/Range of aircraft
Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go Specific Fuel Consumption = (Propeller Efficiency/Range of aircraft)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
Range of Propeller-Driven Airplane for given lift-to-drag ratio
Go Range of aircraft = (Propeller Efficiency/Specific Fuel Consumption)*(Lift-to-drag ratio)*(ln(Gross Weight/Weight without fuel))
Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane
Go Propeller Efficiency = Range of aircraft*Specific Fuel Consumption/(Lift-to-drag ratio*(ln(Gross Weight/Weight without fuel)))
Cruise Weight Fraction for Prop-Driven Aircraft
Go Cruise Weight Fraction = exp((Range of aircraft*(-1)*Specific Fuel Consumption)/(Maximum Lift to Drag Ratio*Propeller Efficiency))
Propeller efficiency for reciprocating engine-propeller combination
Go Propeller Efficiency = Available Power/Brake Power
Shaft brake power for reciprocating engine-propeller combination
Go Brake Power = Available Power/Propeller Efficiency
Power available for reciprocating engine-propeller combination
Go Available Power = Propeller Efficiency*Brake Power
Lift to Drag Ratio for Maximum Endurance given Max Lift to Drag Ratio for Prop-driven Aircraft
Go Lift to Drag Ratio at Maximum Endurance = 0.866*Maximum Lift to Drag Ratio
Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft
Go Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866

Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft Formula

Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866
LDmaxratio = LDEmaxratio/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 given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft?

Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft calculator uses Maximum Lift to Drag Ratio = Lift to Drag Ratio at Maximum Endurance/0.866 to calculate the Maximum Lift to Drag Ratio, Maximum Lift to Drag Ratio given 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 is denoted by LDmaxratio symbol.

How to calculate Maximum Lift to Drag Ratio given 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 given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft, enter Lift to Drag Ratio at Maximum Endurance (LDEmaxratio) and hit the calculate button. Here is how the Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft calculation can be explained with given input values -> 30.02309 = 4.4/0.866.

FAQ

What is Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft?
Maximum Lift to Drag Ratio given 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 LDmaxratio = LDEmaxratio/0.866 or Maximum Lift to Drag Ratio = 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 given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft?
Maximum Lift to Drag Ratio given 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 = Lift to Drag Ratio at Maximum Endurance/0.866. To calculate Maximum Lift to Drag Ratio given Lift to Drag Ratio for Max Endurance of Prop-Driven Aircraft, you need Lift to Drag Ratio at Maximum Endurance (LDEmaxratio). 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?
In this formula, Maximum Lift to Drag Ratio uses Lift to Drag Ratio at Maximum Endurance. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Maximum Lift to Drag Ratio = (Range of aircraft*Specific Fuel Consumption)/(Propeller Efficiency*ln(Weight at Start of Cruise Phase/Weight at End of Cruise Phase))
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