Average Blade Lift Coefficient Calculator

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Aircraft Design

Aircraft Performance

Introduction and Governing Equations

Static Stability and Control

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✖Thrust Coefficient is the ratio of actual thrust to the ideal thrust.ⓘ Thrust Coefficient [C_T]			+10% -10%
✖Rotor Solidity is a function of the aspect ratio and number of blades in the rotor.ⓘ Rotor Solidity [σ]			+10% -10%

✖Blade Lift Coefficient is the lift coefficient of blades and is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body.ⓘ Average Blade Lift Coefficient [C_l]

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Formula

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Average Blade Lift Coefficient

Formula

`"C"_{"l"} = 6*"C"_{"T"}/"σ"`

Example

`"0.4"=6*"0.04"/"0.6"`

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Average Blade Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity
C_l = 6*C_T/σ
This formula uses 3 Variables

Variables Used

Blade Lift Coefficient - Blade Lift Coefficient is the lift coefficient of blades and is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body.
Thrust Coefficient - Thrust Coefficient is the ratio of actual thrust to the ideal thrust.
Rotor Solidity - Rotor Solidity is a function of the aspect ratio and number of blades in the rotor.

STEP 1: Convert Input(s) to Base Unit

Thrust Coefficient: 0.04 --> No Conversion Required
Rotor Solidity: 0.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_l = 6*C_T/σ --> 6*0.04/0.6

Evaluating ... ...

C_l = 0.4

STEP 3: Convert Result to Output's Unit

0.4 --> No Conversion Required

FINAL ANSWER

0.4 <-- Blade Lift Coefficient

(Calculation completed in 00.004 seconds)

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Created by Kaki Varun Krishna

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad

Kaki Varun Krishna has created this Calculator and 25+ more calculators!

Verified by Prasana Kannan

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

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< 9 Structural Design Calculators

Ultimate Tensile Stress for Plate

Go Ultimate Tensile Strength = (Edge Load per Unit Width*Distance between Rivets)/(Plate Thickness*(Distance between Rivets-Diameter of Rivet))

Shear Failure Load on Plate

Go Edge Load per Unit Width = (2*Distance between Rivet and Edge of Plate*Plate Thickness*Maximum Shear Stress)/(Distance between Rivets)

Maximum Blade Efficiency

Go Maximum Blade Efficiency = (2*Blade Lift Force/Blade Drag Force-1)/(2*Blade Lift Force/Blade Drag Force+1)

Allowable Bearing Pressure

Go Bearing Stress = (Edge Load per Unit Width*Distance between Rivets)/(Plate Thickness*Diameter of Rivet)

Shear Load per width

Go Edge Load per Unit Width = (pi*(Diameter^2)*Maximum Shear Stress)/(4*Distance between Rivets)

Joint Efficiency

Go Joint Efficiency for Shell = (Distance between Rivets-Diameter)/(Distance between Rivets)

Disk Loading

Go Load = Aircraft Weight/((pi*Diameter of Rotor^2)/4)

Average Blade Lift Coefficient

Go Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity

Life of Aircraft given Number of Flight

Go Number of Flights = (1/Total Damage per Flight)

Average Blade Lift Coefficient Formula

Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity
C_l = 6*C_T/σ

What is the relation between coefficient of lift and angle of attack?

The lift coefficient of a heli blades varies with angle of attack. Increasing angle of attack is associated with increasing lift coefficient up to the maximum lift coefficient, after which lift coefficient decreases.

How to Calculate Average Blade Lift Coefficient?

Average Blade Lift Coefficient calculator uses Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity to calculate the Blade Lift Coefficient, The Average Blade Lift Coefficient refers to the average value of the lift coefficient across the entire rotor blade of a helicopter or a similar rotary-wing aircraft, the lift coefficient quantifies the lift generation capability of an airfoil and is a crucial parameter in determining the aircraft's performance characteristics. Blade Lift Coefficient is denoted by C_l symbol.

How to calculate Average Blade Lift Coefficient using this online calculator? To use this online calculator for Average Blade Lift Coefficient, enter Thrust Coefficient (C_T) & Rotor Solidity (σ) and hit the calculate button. Here is how the Average Blade Lift Coefficient calculation can be explained with given input values -> 4 = 6*0.04/Solodity_of_rotor_helicopter.

FAQ

What is Average Blade Lift Coefficient?

The Average Blade Lift Coefficient refers to the average value of the lift coefficient across the entire rotor blade of a helicopter or a similar rotary-wing aircraft, the lift coefficient quantifies the lift generation capability of an airfoil and is a crucial parameter in determining the aircraft's performance characteristics and is represented as C_l = 6*C_T/σ or Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity. Thrust Coefficient is the ratio of actual thrust to the ideal thrust & Rotor Solidity is a function of the aspect ratio and number of blades in the rotor.

How to calculate Average Blade Lift Coefficient?

The Average Blade Lift Coefficient refers to the average value of the lift coefficient across the entire rotor blade of a helicopter or a similar rotary-wing aircraft, the lift coefficient quantifies the lift generation capability of an airfoil and is a crucial parameter in determining the aircraft's performance characteristics is calculated using Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity. To calculate Average Blade Lift Coefficient, you need Thrust Coefficient (C_T) & Rotor Solidity (σ). With our tool, you need to enter the respective value for Thrust Coefficient & Rotor Solidity 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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