Maximum Lift over Drag Calculator

✖Landing Mass Fraction is a constant that depends on the various different aircraft types.ⓘ Landing Mass Fraction [K_LD]			+10% -10%
✖The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a Wing [AR]			+10% -10%
✖The Aircraft Wetted Area is the surface area that interacts with the working fluid or gas.ⓘ Aircraft Wetted Area [S_wet]			+10% -10%
✖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.ⓘ Reference Area [S]			+10% -10%

✖Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.ⓘ Maximum Lift over Drag [LDmax_ratio]

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Formula

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Maximum Lift over Drag

Formula

`"LDmax"_{"ratio"} = "K"_{"LD"}*(("AR")/("S"_{"wet"}/"S"))^(0.5)`

Example

`"19.79899"="14"*(("4")/("10.16m²"/"5.08m²"))^(0.5)`

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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)
LDmax_ratio = K_LD*((AR)/(S_wet/S))^(0.5)
This formula uses 5 Variables

Variables Used

Maximum Lift-to-Drag Ratio of Aircraft - Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.
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

LDmax_ratio = K_LD*((AR)/(S_wet/S))^(0.5) --> 14*((4)/(10.16/5.08))^(0.5)

Evaluating ... ...

LDmax_ratio = 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)

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Created by Prasana Kannan

Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai

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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 Optimum 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 Preliminary 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 = Harmonic Range-Range Increment of Aircraft

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)
LDmax_ratio = K_LD*((AR)/(S_wet/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 represents the efficiency of an aircraft or airfoil in generating lift compared to the drag it produces, this formula calculates the maximum lift-to-drag ratio by considering the landing mass fraction, aspect ratio of the wing, and the ratio of the wetted area of the aircraft to the reference area, with appropriate scaling factors. Maximum Lift-to-Drag Ratio of Aircraft is denoted by LDmax_ratio 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 (K_LD), Aspect Ratio of a Wing (AR), Aircraft Wetted Area (S_wet) & 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 represents the efficiency of an aircraft or airfoil in generating lift compared to the drag it produces, this formula calculates the maximum lift-to-drag ratio by considering the landing mass fraction, aspect ratio of the wing, and the ratio of the wetted area of the aircraft to the reference area, with appropriate scaling factors and is represented as LDmax_ratio = K_LD*((AR)/(S_wet/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 represents the efficiency of an aircraft or airfoil in generating lift compared to the drag it produces, this formula calculates the maximum lift-to-drag ratio by considering the landing mass fraction, aspect ratio of the wing, and the ratio of the wetted area of the aircraft to the reference area, with appropriate scaling factors 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 (K_LD), Aspect Ratio of a Wing (AR), Aircraft Wetted Area (S_wet) & 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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