| 摘要 |
<p>Disclosed is a design method for a three-dimensional curved airfoil section. The method comprises the following steps: collecting arc coordinate data of a conventional 2D airfoil section such as (x1, y1) and (x2, y2); according to the conventional airfoil section coordinate data, calculating an increment such asΔL1 andΔL2 between each x coordinate point of a chord; determining a radius of rotation R of the airfoil section to be arranged according to the design; selecting x1=z1=0.707R, where y1=0; inserting x1, z1,ΔL1 and R into a specific formula to calculate x2 and z2, thereby creating a three-dimensional airfoil section arc coordinate (x2, y2, z2), wherein y2 is still a coordinate value of the thickness of the 2D airfoil section; and by this analogy, calculating a three-dimensional airfoil section arc coordinate cluster (x3, y3, z3), etc. This method improves the aerodynamic profile of a blade by means of optimising a three-dimensional curved airfoil section, thereby increasing aerodynamic force efficiency of a rotary blade on the basis of the same materials and structural arrangement.</p> |
