Maximum Lift over Drag Solution

STEP 0: Pre-Calculation Summary
Formula Used
Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5)
LDmaxratio = KLD*((AR)/(Swet/S))^(0.5)
This formula uses 5 Variables
Variables Used
Maximum Lift to Drag Ratio of Aircraft - Maximum Lift to Drag ratio of Aircraft while in cruise, the ratio of lift to drag coefficient is maximum in value.
Landing Mass Fraction - Landing Mass Fraction is a constant that depends on the various different aircraft types.
Aspect Ratio of a Wing - The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
Aircraft Wetted Area - (Measured in Square Meter) - The Aircraft Wetted Area is the surface area that interacts with the working fluid or gas.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
STEP 1: Convert Input(s) to Base Unit
Landing Mass Fraction: 14 --> No Conversion Required
Aspect Ratio of a Wing: 4 --> No Conversion Required
Aircraft Wetted Area: 10.16 Square Meter --> 10.16 Square Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
LDmaxratio = KLD*((AR)/(Swet/S))^(0.5) --> 14*((4)/(10.16/5.08))^(0.5)
Evaluating ... ...
LDmaxratio = 19.7989898732233
STEP 3: Convert Result to Output's Unit
19.7989898732233 --> No Conversion Required
FINAL ANSWER
19.7989898732233 19.79899 <-- Maximum Lift to Drag Ratio of Aircraft
(Calculation completed in 00.004 seconds)

Credits

Created by Prasana Kannan
Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai
Prasana Kannan has created this Calculator and 25+ more calculators!
Verified by Kaki Varun Krishna
Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
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25 Preliminary Design Calculators

Velocity at Maximum Endurance given Preliminary Endurance for Prop-Driven Aircraft
Go 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)
Preliminary Endurance for Prop-Driven Aircraft
Go 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)
Velocity for Maximizing Range given Range for Jet Aircraft
Go Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift to Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))
Optimum Range for Jet Aircraft in Cruising Phase
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)
Optimum Range for Prop-Driven Aircraft in Cruising Phase
Go Range of Aircraft = (Propeller Efficiency*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 Endurance for Jet Aircraft
Go Endurance of Aircraft = (Maximum Lift to Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))/Power Specific Fuel Consumption
Maximum Lift over Drag
Go Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5)
Preliminary Take Off Weight Built-up for Manned Aircraft
Go Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight
Payload Weight given Takeoff Weight
Go Payload Carried = Desired Takeoff Weight-Operating Empty Weight-Crew Weight-Fuel Weight to be Carried
Empty Weight given Takeoff Weight
Go Operating Empty Weight = Desired Takeoff Weight-Fuel Weight to be Carried-Payload Carried-Crew Weight
Crew Weight given Takeoff Weight
Go Crew Weight = Desired Takeoff Weight-Payload Carried-Fuel Weight to be Carried-Operating Empty Weight
Fuel Weight given Takeoff Weight
Go Fuel Weight to be Carried = Desired Takeoff Weight-Operating Empty Weight-Payload Carried-Crew Weight
Preliminary Take off Weight Built-Up for Manned Aircraft given Fuel and Empty Weight Fraction
Go Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction)
Fuel Fraction given Takeoff Weight and Empty Weight Fraction
Go Fuel Fraction = 1-Empty Weight Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight
Empty Weight Fraction given Takeoff Weight and Fuel Fraction
Go Empty Weight Fraction = 1-Fuel Fraction-(Payload Carried+Crew Weight)/Desired Takeoff Weight
Payload Weight given Fuel and Empty Weight Fractions
Go Payload Carried = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Crew Weight
Crew Weight given Fuel and Empty Weight Fraction
Go Crew Weight = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Payload Carried
Takeoff Weight given Empty Weight Fraction
Go Desired Takeoff Weight = Operating Empty Weight/Empty Weight Fraction
Empty Weight given Empty Weight Fraction
Go Operating Empty Weight = Empty Weight Fraction*Desired Takeoff Weight
Empty Weight Fraction
Go Empty Weight Fraction = Operating Empty Weight/Desired Takeoff Weight
Winglet Friction Coefficient
Go Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58))
Takeoff Weight given Fuel Fraction
Go Desired Takeoff Weight = Fuel Weight to be Carried/Fuel Fraction
Fuel Weight given Fuel Fraction
Go Fuel Weight to be Carried = Fuel Fraction*Desired Takeoff Weight
Fuel Fraction
Go Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight
Design range given range increment
Go Design range = Range increment of aircraft+Harmonic range

Maximum Lift over Drag Formula

Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5)
LDmaxratio = KLD*((AR)/(Swet/S))^(0.5)

What is drag and lift?

Lift is defined as the component of the aerodynamic force that is perpendicular to the flow direction, and drag is the component that is parallel to the flow direction.

How to Calculate Maximum Lift over Drag?

Maximum Lift over Drag calculator uses Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5) to calculate the Maximum Lift to Drag Ratio of Aircraft, The Maximum Lift over Drag formula directly and mainly the fuel and battery weight estimation. The Landing mass fraction varies wrt different aircraft types. Maximum Lift to Drag Ratio of Aircraft is denoted by LDmaxratio symbol.

How to calculate Maximum Lift over Drag using this online calculator? To use this online calculator for Maximum Lift over Drag, enter Landing Mass Fraction (KLD), Aspect Ratio of a Wing (AR), Aircraft Wetted Area (Swet) & Reference Area (S) and hit the calculate button. Here is how the Maximum Lift over Drag calculation can be explained with given input values -> 19.79899 = 14*((4)/(10.16/5.08))^(0.5) .

FAQ

What is Maximum Lift over Drag?
The Maximum Lift over Drag formula directly and mainly the fuel and battery weight estimation. The Landing mass fraction varies wrt different aircraft types and is represented as LDmaxratio = KLD*((AR)/(Swet/S))^(0.5) or Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5). Landing Mass Fraction is a constant that depends on the various different aircraft types, The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord, The Aircraft Wetted Area is the surface area that interacts with the working fluid or gas & The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
How to calculate Maximum Lift over Drag?
The Maximum Lift over Drag formula directly and mainly the fuel and battery weight estimation. The Landing mass fraction varies wrt different aircraft types is calculated using Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5). To calculate Maximum Lift over Drag, you need Landing Mass Fraction (KLD), Aspect Ratio of a Wing (AR), Aircraft Wetted Area (Swet) & Reference Area (S). With our tool, you need to enter the respective value for Landing Mass Fraction, Aspect Ratio of a Wing, Aircraft Wetted Area & Reference Area 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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