INVESTIGATION OF COMPOUND HELICOPTER AERODYNAMIC INTERFERENCE EFFECTS
Abstract
A generalized model of a compound helicopter was tested in a 18-foot wind tunnel to determine the nature of aerodynamic interferences between the rotor, the fuselage, and various wings, as well as the effects of these components on the downwash at the tail. In addition, a theoretical method for calculating the wing induced flow through the rotor is presented, and the theoretical results are correlated with the experimental results. In a second test the mutual interferences between a rotor and various propeller configurations were investigated. It was concluded from this work that the vibratory bending moments on wing-mounted tractor propellers are a direct function of the sum of the rotor momentum downwash angle and the geometric angle of attack while the vibratory bending moments on a tail-mounted pushed propeller have a relationship to the rotor lift which depends on the presence or absence of empennage forward of the propeller. It was also found that increasing thrust on wing-mounted tractor propellers generally causes increased rotor blade vibratory bending moments.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1967
- Accession Number
- AD0665427
Entities
People
- Anton J. Landgrebe
- Lawrence J. Bain
Organizations
- United Technologies Corporation