Method of Determining Propeller Pitch Stops for a FAR 23 Airplane Dept. of Mech. and Aeronautical Engrg., Western Michigan Univ

Format:

Book

Conference/Event

Author/Creator:

Biber, Kasim, author.

Conference Name:

General Avaition Technology Conference & Exposition (2000-05-09 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource cm

Place of Publication:

Warrendale, PA SAE International 2000

Summary:

This paper presents a method of predicting propeller speed and pitch stops of a twin turbine engine airplane, driven by a single propeller under FAR 23-commuter category regulation. The analysis includes integration of propeller and engine performance models with an example airframe. The propeller blade angle varied for its operational range at 75% disk radius in order to observe changes in powerplant performance within the airplane flight envelope. Performance data were generated to show the limitations in propeller pitch angle and rotational speed, engine power and flight speed. The prediction method should serve as guidance for those who work in preliminary design of a turboprop airplane

Notes:

Vendor supplied data

Publisher Number:

2000-01-1692

Access Restriction:

Restricted for use by site license