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Lift Engine Technology
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English
Abstract
The following points, discussed in this paper, should be considered very carefully in all systems contemplating the use of lift engines for VTOL aircraft: (1) The rate of benefit to the aircraft decreases rapidly for engine thrust-to-weight ratios greatly in excess of 20:1; (2) Working relationships are available for use in the aeromechanical design phase of high thrust-to-weight ratio engines; (3) The “installed” thrust-to-weight ratio of lift engines is the most important criterion for evaluation of alternative peripheral equipment design concepts; (4) The reaction control, thrust vectoring, and induction subsystems contribute most of the degradation of lift engine “installed” thrust-to-weight; (5) The rotating cascade concept is the most promising system for deflecting lift engine exhaust flow to achieve both vehicle control and STOL capability; (6) The jetevator, vane deflectors and spherical nozzle concepts are competitive within specified deflection angle ranges; (7) Scoop-type inlets with movable vanes in the upper surface can be devised to alleviate lift engine induction losses; and (8) Significant improvements in the lift engine installed volume can be obtained by optimizing the inlet lip and engine vertical location within the fuselage or engine pod.
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Authors
Topic
Citation
Foster, T. and Paget, H., "Lift Engine Technology," SAE Technical Paper 650201, 1965, https://doi.org/10.4271/650201.Also In
References
- Bairstow L. “Applied Aerodynamics.” London Long-mans Green and Co 1939
- Kussoy M. I. Bachkin D. “Comparison of Performance of Two Aerodynamically Similar 14-Inch-Diameter Single Stage Compressor Rotors of Different Chord Length.” 1958
- Bagby C. L. “Considerations of Lift Engine Installations in VTOL Aircraft from the Viewpoint of the Airframe Designer,” SAE Paper 635A January 1963
- Tyson B. I. “Tests of Air Inlets for Jet Lift Engines,” SAE Paper 860B April 1964
- Tyson B. I. “Tests to Establish Flow Distortion Criteria for Lift Engines,” American Institute of Aeronautics & Astronautics Paper August 1964