Winglet Friction Coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58))
μfriction = 4.55/(log10(Rewl^2.58))
This formula uses 1 Functions, 2 Variables
Functions Used
log10 - The common logarithm, also known as the base-10 logarithm or the decimal logarithm, is a mathematical function that is the inverse of the exponential function., log10(Number)
Variables Used
Coefficient of Friction - The Coefficient of Friction (μ) is the ratio defining the force that resists the motion of one body in relation to another body in contact with it.
Winglet Reynolds Number - Winglet Reynolds number is based on a length, which is usually the chord length of an airfoil (in two dimensions) or the chord length of a winglet.
STEP 1: Convert Input(s) to Base Unit
Winglet Reynolds Number: 5000 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
μfriction = 4.55/(log10(Rewl^2.58)) --> 4.55/(log10(5000^2.58))
Evaluating ... ...
μfriction = 0.476772152627779
STEP 3: Convert Result to Output's Unit
0.476772152627779 --> No Conversion Required
FINAL ANSWER
0.476772152627779 0.476772 <-- Coefficient of Friction
(Calculation completed in 00.004 seconds)

Credits

Created by Kaki Varun Krishna
Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
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National Institute Of Technology (NIT), Hamirpur
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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

Winglet Friction Coefficient Formula

Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58))
μfriction = 4.55/(log10(Rewl^2.58))

What are winglets?

Winglets are vertical extensions of wingtips that improve an aircraft's fuel efficiency and cruising range

How to Calculate Winglet Friction Coefficient?

Winglet Friction Coefficient calculator uses Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58)) to calculate the Coefficient of Friction, The Winglet friction coefficient formula is defined as the friction coefficient between the fully turbulent boundary layer and the winglet. Coefficient of Friction is denoted by μfriction symbol.

How to calculate Winglet Friction Coefficient using this online calculator? To use this online calculator for Winglet Friction Coefficient, enter Winglet Reynolds Number (Rewl) and hit the calculate button. Here is how the Winglet Friction Coefficient calculation can be explained with given input values -> 0.476772 = 4.55/(log10(5000^2.58)).

FAQ

What is Winglet Friction Coefficient?
The Winglet friction coefficient formula is defined as the friction coefficient between the fully turbulent boundary layer and the winglet and is represented as μfriction = 4.55/(log10(Rewl^2.58)) or Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58)). Winglet Reynolds number is based on a length, which is usually the chord length of an airfoil (in two dimensions) or the chord length of a winglet.
How to calculate Winglet Friction Coefficient?
The Winglet friction coefficient formula is defined as the friction coefficient between the fully turbulent boundary layer and the winglet is calculated using Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58)). To calculate Winglet Friction Coefficient, you need Winglet Reynolds Number (Rewl). With our tool, you need to enter the respective value for Winglet Reynolds Number 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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