An investigation of two-propeller tilt wing V/STOL aircraft flight characteristics
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Authors
Neiusma, William J., Jr.
Subjects
Tilt wing VSTOL aircraft
TWANG
TLTWNG!!
Longitudinal pitch attitude
Longitudinal stick position
Elevator position
TWANG
TLTWNG!!
Longitudinal pitch attitude
Longitudinal stick position
Elevator position
Advisors
Newberry, Conrad F.
Corliss, Lloyd D.
Churchill, Gary F.
Date of Issue
1993-06
Date
June 1993
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
The results of a two-propeller tilt wing aircraft static stability and performance simulation utilizing a NASA-Ames computer code, Tilt Wing Application General (TWANG), are presented with comparisons to actual test flight data. The Canadair CL-84 tilt wing aircraft was used as a model for the geometric data utilized by the computer simulation. Aerodynamic data for the simulation were obtained from previous NASA Ames research related to a four-propeller model. Variables used included a wide range of parameters associated with flight conditions from hovering flight to maximum cruise speeds at several different altitudes and wing tilt configurations. Longitudinal pitch stability was the driving factor in determining aircraft static stability for the various flight conditions. Results of the simulation indicate that the TWANG computer code provides an accurate prediction of both generic and specific tilt wing aircraft static pitch performance characteristics, as well as the additional capability of providing the required mathematical parameters for incorporation into the NASA Ames Vertical Motion Simulator as software inputs.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
viii, 80 p.: ill.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.