Rotor Blade Designs and Planforms

This design features a symmetrical airfoil shape, resulting in consistent aerodynamic characteristics throughout the blade.

This design uses an airfoil with a higher camber on one side than the other, creating greater lift for the same surface area.

This planform has the leading and trailing edges running parallel to each other, creating a uniform chord length.

This planform features a converging leading and trailing edge, with the chord length decreasing towards the blade root.

This type of construction involves bonding the rotor blade skin to the ribs, resulting in stronger and more durable blades.

This skin configuration uses a single large skin panel that covers the entire blade, making it faster to build.

This skin configuration uses multiple smaller skin panels, allowing for easier repair since only the damaged panel needs replacement.

This type of weight is used to adjust blade balance and trim, typically placed at the tip of the rotor blade.

Erosion of rotor blades can occur due to dust particles in the air, and stainless steel capping on the leading edge provides protection against this.

The dark paint helps reduce glare from the sun, improving the pilot's visibility.

Composite blades are designed with static discharge properties to prevent the build-up of static electricity, which can disrupt flight operations.

Tap testing is a non-destructive inspection method used to detect damage or defects in the composite material of rotor blades.

Adding additional plates at the root of the tip increases the structural strength without adding weight, providing greater stability to the blade.

Spanwise balance weights are located at the center of the blade tip, along the spanline, to counteract any imbalances that might occur during rotation.

Chordwise mass balance weights are positioned along the leading edge of the blade, typically between 30 to 50 percent of the blade's length, to ensure proper balance.

Trim tabs are aerodynamic control surfaces located at the trailing edge of the blade. They are designed to adjust the blade's lift and pitch, allowing for precise control of the helicopter's flight.

A small airfoil on the trailing edge of each rotor blade, located at about 75% of the blade span. It's positioned for maximum aerodynamic reaction.

It eliminates the need for hydraulic systems, improving simplicity and reliability. Provides infinite life, reducing maintenance.

They are connected to the throttle mechanism, allowing for precise control of engine power in accordance with collective pitch changes.

It automatically adjusts the engine power to compensate for lag when the pilot changes collective pitch.

A device used to dampen vibrations in the helicopter's main rotor system.

A vibration absorbing device located at the hub of the main rotor system.

It returns the cyclic control to its previous position after a pilot input, providing a stable and comfortable flight experience.

An inverted airfoil designed to provide downwards lift, improving stability and smoothness during flight.