DRAG PROFILE DRAG THRUST INDUCED DRAG Aircraft Yaw—The movement of the helicopter about its vertical axis. 2-5 Figure 2-12. It is easy to visualize the creation of form drag by examining the airflow around a flat plate. Streamlining decreases form drag by reducing the airflow separation. Figure 2-11. The load factor diagram allows you to calculate the amount of “G” loading exerted with various angle of bank. The force that resists the movement of a helicopter through the air and is produced when lift is developed is called drag. Drag always acts parallel to the relative wind. Total drag is composed of three types of drag: profile, induced, and parasite. Profile drag develops from the frictional resistance of the blades passing through the air. It does not change significantly with the airfoil’s angle of attack, but increases moderately when airspeed increases. Profile drag is composed of form drag and skin friction. Form drag results from the turbulent wake caused by the separation of airflow from the surface of a struc- ture. The amount of drag is related to both the size and shape of the structure that protrudes into the relative wind. [Figure 2-12] Skin friction is caused by surface roughness. Even though the surface appears smooth, it may be quite rough when viewed under a microscope. A thin layer of air clings to the rough surface and creates small eddies that contribute to drag. Thrust, like lift, is generated by the rotation of the main rotor system. In a helicopter, thrust can be for- ward, rearward, sideward, or vertical. The resultant of lift and thrust determines the direction of movement of the helicopter. The solidity ratio is the ratio of the total rotor blade area, which is the combined area of all the main rotor blades, to the total rotor disc area. This ratio provides a means to measure the potential for a rotor system to provide thrust. Induced drag is generated by the airflow circulation around the rotor blade as it creates lift. The high-pres- sure area beneath the blade joins the low-pressure air above the blade at the trailing edge and at the rotor tips. This causes a spiral, or vortex, which trails behind each blade whenever lift is being produced. These vortices deflect the airstream downward in the vicinity of the blade, creating an increase in downwash. Therefore, the blade operates in an average relative wind that is inclined downward and rearward near the blade. Because the lift produced by the blade is perpendicular The tail rotor also produces thrust. The amount of thrust is variable through the use of the antitorque ped- als and is used to control the helicopter’s  yaw . Load Factor - "G's" Bank Angle (in Degrees) 0 10 20 30 40 50 60 70 80 90 9 8 7 6 5 4 3 2 1 0