This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Synthesis of Future High Lift Systems
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1970 by SAE International in United States
Annotation ability available
The subject of high lift systems is extremely broad and therefore must be restricted in order to be tractable. For the purposes of this paper, it is felt to be sufficient to consider four-engine M = 0.8 turbofan aircraft with about 1800-ft FAA field length capability. Even with the foregoing limitations on scope, it is only possible to present what are felt to be the essential concepts at the edge of the propulsion, aerodynamic, and design elements of the subject.
The analysis indicates that:
When there is a need for turbofan STOL aircraft capable of operation from 1800-ft fields, this need can be satisfied by aircraft that are similar in size and proportions to current conventional aircraft. Propulsion developments in process are expected to yield engines with excellent thrust matching between low-speed and high-speed requirements. The weights and noise of these engines are expected to be completely acceptable. Efficient cascade-type thrust deflectors suitable for the resulting high-bypass engines also appear possible.
In order to use conventional wing loadings and aspect ratios, maximum lift coefficients must approach the theoretical limit of circulation lift. Projected developments in variable-geometry, blowing BLC leading edge slats, combined with blowing BLC trailing edge flaps, are expected to provide the needed improvements.
The propulsion and aerodynamic trends that could result in a family of 24 possible high lift systems appear to contain only three acceptable members. The one acceptable first-generation concept provides a basis for evolution to the two possible second-generation systems, possibly with a common airframe.
CitationScherrer, R., "Synthesis of Future High Lift Systems," SAE Technical Paper 700811, 1970, https://doi.org/10.4271/700811.
- Lachmann G. V. “Boundary Layer and Flow Control.” I II New York Pergamon Press 1961
- Williams J. Butler S. F. J. “Aerodynamic Aspects of Boundary Layer Control for High Lift at Low Speeds.” AGARD Report 414 January 1963
- McCormick, B. W. Jr. “Aerodynamics of V/STOL Flight.” New York Academic Press 1967
- Wimpenny J. C. “The Design and Application of High Lift Devices.” Annals of the New York Academy of Sciences 1967
- Weir R. H. “Propulsion Prospects.” 16th Barnwell Memorial Lecture, The Aeronautical Journal, Royal Aeronautical Society November 1969 923 934
- Sens W. H. Meyer R. M. “New Generation Engines-The Engine Manufacturer's Outlook.” Paper 680278 presented at SAE Air Transportation Meeting New York April 1968
- Rosen G. “Filling the Propulsion Gaps.” Space/Aeronautics May 1970 32 38
- “Variable-Pitch Fan Designed for Low-Noise STOL Aircraft.” Aviation Week and Space Technology September 14 1970 66
- Lockheed-California Company “Conceptual Commercial STOL Transportation Systems.” Report LR 22993 November 17 1969
- “Tandem Cascade Thrust Vectoring Research Program.” General Electric Co. Report R-64-FPD November 1964
- Hammond A. D. McLemore H. C. “Hot Gas Injestion and Jet Interference Effects.” AGARD Flight Mechanics Panel Meeting September 1967
- Williams J. June 1966
- Hickey D. H. Kirk J. V. Hall L. P. “Aerodynamic Characteristics of a V/STOL Transport Model with Lift and Cruise-Fan Power Plants.” NASA Conference on V/STOL and STOL Aircraft April 4-5 1966 81 96
- Thomas F. “Investigations Into Increasing The Lift of Wings by Boundary Layer Control Through Blowing.” Flugwiss Z. 10 2 1962 46 65 Royal Aircraft Establishment Library Translation No. 1267
- Fink M. P. McLemore H. C. “High Pressure Blowing Over Flap and Wing Leading Edge of a Thin Large Scale 49° Swept Wing-Body-Tail Configuration in Combination with a Drooped Nose and a Nose with a Radius Increase.” NACA May 28 1957
- Siewert R. F. Stewart V. R. “Use of Boundary Layer Control on a Supersonic Attack-Reconnaissance Aircraft.” AIAA J. Aircraft 4 2 March-April 1967
- Hickey D. H. Aoyagi K. “Large-Scale Wind Tunnel Tests of an Airplane Model with a 45° Sweptback Wing of Aspect Ratio 2.8 Employing High Velocity Blowing Over the Leading and Trailing Edge Flaps.” NACA May 26 1958
- Maki R. L. Giulianetti D. J. “Low-Speed Wind Tunnel Investigation of Blowing Boundary Layer Control on Leading and Trailing Edge Flaps of a Full Scale Low Aspect Ratio, 42° Swept-Wing Airplane Configuration.” NASA August 1959
- James H. A. Maki R. L. “Wind Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept Wing Airplane Blowing Flaps and Leading Edge Slats.” NACA
- Kelly M. W. Tolhurst, W. H. Jr. Maki R. L. “Full-Scale Wind Tunnel Tests of a Low Aspect Ratio Straight Wing Airplane with Blowing Boundary Layer Control on Leading- and Trailing-Edge Flaps.” NASA September 1959
- Head M. R. Clark D. G. “Flight Experiments on Suction for High Lift,” AIAA J. Aircraft 4 2 March-April 1969
- Butler S. F. J. Lawford J. A. “Low Speed Wind Tunnel Tests on a Wing Fuselage Model with Area Suction Through Perforations at the Leading Edge Flap Knee.” R.A.E. July 1967
- McLemore H. C. Fink M.P. “Blowing Over the Flaps and Wing Leading Edge of a Thin 49° Swept Wing-Body-Tail Configuration in Combination with Leading Edge Devices.” NACA July 20 1956
- Anderson S. B. Faye, A. E. Jr. Innis R. C. “Flight Investigation of the Low Speed Characteristics of a 35° Swept-Wing Airplane Equipped with an Area Suction Ejector Flap and Various Wing Leading Edge Devices.” NACA September 26 1957
- McLemore H. C. Peterson, J. B. Jr. “Aerodynamic Characteristics of a Large-Scale Unswept Wing-Body-Tail Configuration with Blowing Applied Over the Flap and Wing Leading Edge.” NASA September 1960
- “Wind Tunnel Tests of a Lockheed GL- 128 (BLC C-130) Airplane.” United Aircraft Report R-1546-1
- Lowry J. G. Polhamus E. C. “A Method for Predicting Lift Increments Due to Flap Deflection at Low Angles of Attack in Incompressible Flow.” NACA January 1957
- Chaplin H. R. “Preliminary Wind Tunnel Investigation of a Method of Suppressing The Leading Edge Stall on a Wing by Tangential Blowing.” U.S. Navy, David Taylor Model Basin, Aerodynamics Laboratory Aero Report 894 March 1956
- Bowling H. T. Hurkamp C. H. Thornton R. M. “Optimizing the Propulsion/Lift System for Turbofan STOL Aircraft.” Paper 69-1131 presented at AIAA Sixth Annual Meeting Anaheim, California October 20-24 1969