Application of the Vortex-Lattice Method to Propeller Performance Analysis
Abstract
The objective of this thesis is to examine the feasibility of applying a vortex lattice method to propeller performance analysis. This method allows the calculation of spanwise and chordwise pressure distributions on thin propeller blades of arbitrary planform. The research for this project involves the application of a vortex lattice method to a propeller with twisted, non- cambered, constant chord blades. The analysis assumes incompressible, inviscid flow over thin sections. The helical wake is modeled as a series of straight vortex filament segments. A computer code has been developed which uses a vortex lattice method to predict performance for propellers. Results are shown for several operating conditions, using various angle of attack distributions, numbers of blades on the propeller, and advance ratios. Similar results are shown using the blade-element theory for comparison. Results indicate that this vortex lattice method is applicable to initial propeller performance analysis.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1982
- Accession Number
- ADA124837
Entities
People
- Marc L. Masquelier
Organizations
- Air Force Institute of Technology