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Maximum Lift over Drag Calculator

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Preliminary Design Conceptual Design

✖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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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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< 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

Maximum Lift over Drag Formula

LaTeX Go

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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