TABLES OF AERODYNAMIC DERIVATIVES OF OSCILLATING ROTOR BLADES IN HOVERING FLIGHT,
Abstract
A theory was developed for determining the influence of compressibility on the aerodynamic forces acting on helicopter rotor blades when oscillating in hovering flight. In this theory, the usual two-dimensional mathematical model of the flow was adopted in which a section of the reference rotor balde and its helical wake are replaced by an airfoil with a straight wake and a system of regularly spaced infinite wakes below, the amount of spacing depending on the downward flow induced by the rotor and the number of blades. In this report, the same theory is used to compute the aerodynamic derivative coefficients referred to the quarter-chord point on the airfoil. The results obtained are tabulated for single and two-bladed rotors for a range of values of the parameters involved. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1969
- Accession Number
- AD0697177
Entities
People
- B. M. Rao
- W. P. Jones
Organizations
- Texas A&M University