New Development of Classical Actuator Disk Model for Propellers at Incidence (2020)

View/ Open
Type of Content
Journal ArticleISSN
0001-1452Collections
Abstract
The actuator disk model thrust formula was mathematically expanded in series and divided into two parts to show that propellers at incidence comprise an axial and a wing lift equivalent component. Both components share a common induced speed w. This is done by considering an enhanced disk area for momentum balance, to match Glauert’s hypothesis mass flowrate. To shed light on the theoretical developments, wind tunnel tests were conducted on a two-bladed propeller at angles of incidence ranging from 0 to 90 deg. The wing component is shown to increase with airflow velocity and angle of incidence. The axial component decreases with V, for all angles. The generally observed thrust increase with angle of incidence is explained, by the theory, to be mostly due to the wing component contribution. The theory also explains why at around an angle of incidence of 60 deg propellers inherently behave differently than at lower angles. While thrust decreases with V at lower angles, it grows with airspeed at an angle of 2 incidence of approximately 60 deg or higher. This behavioral inversion happens as the wing component positive sensitivity to V overcomes the negative sensitivity of the axial component. A simplified formula is presented for predicting thrust at a given angle, based only on propellers data at an angle of incidence of 0, regardless of blade geometry.
Citation
Rubin RL, Zhao D, (2020). New Development of Classical Actuator Disk Model for Propellers at Incidence. AIAA Journal: devoted to aerospace research and development.This citation is automatically generated and may be unreliable. Use as a guide only.
ANZSRC Fields of Research
40 - Engineering::4001 - Aerospace engineeringRights
All rights reserved unless otherwise statedRelated items
Showing items related by title, author, creator and subject.
-
Effects of the foam metal casing treatment on aerodynamic stability and aerocoustic noise in an axial flow compressor
Sun D; Li J; Xu R; Dong X; Zhao D; Sun X; ZHAO, DAN (Elsevier BV, 2021)A kind of foam metal casing treatment (FMCT) is proposed and experimentally tested on a low-speed axial flow compressor in this work. Foam metal is a foam-like substance with a lightweight structure but a certain strength. ... -
Effects of baffle designs on damping acoustic oscillations in a solid rocket motor
Han L; Li J; Gu X; Ma B; Wang N; ZHAO, DAN (Elsevier BV, 2021)The baffle is a practical and promising passive damping method of dissipating acoustic energy and increasing acoustic losses in a solid rocket motor (SRM). In this study, numerical studies were conducted conjunction with ... -
A Transient, Multi-Scale, Heterogeneous Model of Hydrogen Peroxide Decomposition for 3D-Printed Catalysts
Reid S; Symons D; Watson, Matthew (2022)Hydrogen peroxide thrusters rely on catalysts to generate steam and oxygen, and yet relatively little is known about the processes that occur within the catalyst bed. Previous models have assumed that both diffusional ...