Average Blade Lift Coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity
Cl = 6*CT/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
Cl = 6*CT/σ --> 6*0.04/0.6
Evaluating ... ...
Cl = 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)

Credits

Created by Kaki Varun Krishna
Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
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Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai
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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
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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)
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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
Cl = 6*CT/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 formula is the mean 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. Blade Lift Coefficient is denoted by Cl 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 (CT) & 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 formula is the mean 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 and is represented as Cl = 6*CT 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 formula is the mean 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 is calculated using Blade Lift Coefficient = 6*Thrust Coefficient/Rotor Solidity. To calculate Average Blade Lift Coefficient, you need Thrust Coefficient (CT) & 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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