Optimal Pitch Thrust-Vector Angle and Benefits for all Flight Regimes

Gilyard, Glenn B. and Bolonkin, Alexander (2000) Optimal Pitch Thrust-Vector Angle and Benefits for all Flight Regimes. Technical Report NASA/TM-2000-209021, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

The NASA Dryden Flight Research Center is exploring the optimum thrust-vector angle on aircraft. Simple aerodynamic performance models for various phases of aircraft flight are developed and optimization equations and algorithms are presented in this report. Results of optimal angles of thrust vectors and associated benefits for various flight regimes of aircraft (takeoff, climb, cruise, descent, final approach, and landing) are given. Results for a typical wide-body transport aircraft are also given. The benefits accruable for this class of aircraft are small, but the technique can be applied to other conventionally configured aircraft. The lower L/D aerodynamic characteristics of fighters generally would produce larger benefits than those produced for transport aircraft.

EPrint Type:	NASA Technical Memorandum
Keywords:	Commercial aircraft, Efficiency, Lift-to-drag ratio, Optimization, Thrust vectoring
Subjects:	Aircraft/Project: Nonaircraft-specific (01 - 09) Aeronautics: (02) Aerodynamics (01 - 09) Aeronautics: (03) Air Transportation And Safety
ID Code:	72
Deposited On:	12 July 2004
Additional Information:	27 pages. Glenn B. Gilyard, NASA Dryden Flight Research Center, Edwards, California and Alexander Bolonkin, Senior Research Associate of the National Research Council, Edwards, California.