This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Hybrid Laminar Flow Control Applied to Advanced Turbofan Engine Nacelles
Annotation ability available
Sector:
Language:
English
Abstract
In recent years, the National Aeronautics and Space Administration (NASA) in cooperation with U.S. industry has performed flight and wind-tunnel investigations aimed at demonstrating the feasibility of obtaining significant amounts of laminar boundary-layer flow at moderate Reynolds numbers on the swept-back wings of commercial transport aircraft. Significant local drag reductions have been recorded with the use of a hybrid laminar flow control (HLFC) concept. In this paper, we address the potential application of HLFC to the external surface of an advanced, high bypass ratio turbofan engine nacelle with a wetted area which approaches 15 percent of the wing total wetted area of future commercial transports. A pressure distribution compatible with HLFC is specified and the corresponding nacelle geometry is computed utilizing a predictor/corrector design method. Linear stability calculations are conducted to provide predictions of the extent of the laminar boundary layer. Performance studies on an advanced twin-engine transport configuration are presented to determine potential benefits in terms of reduced fuel consumption.
Recommended Content
Authors
Citation
Collier, F., Arcara, P., and Wie, Y., "Hybrid Laminar Flow Control Applied to Advanced Turbofan Engine Nacelles," SAE Technical Paper 920962, 1992, https://doi.org/10.4271/920962.Also In
References
- Hefner, J. N. Bushnell, D. M. “Application of Stability Theory to Laminar Flow Control,” AIAA Paper 79-1493 AIAA 12th Fluid and Plasma Dynamics Conference Williamsburg, Va. July 1979
- Wagner, R. D. Maddalon, D. V. Bartlett, D. W. Collier, F. S., Jr. “Fifty Years of Laminar Flow Flight Testing,” SAE Paper No. 881393 1988
- Vijgen, P. M. H. W. Dodbele S. S. Holmes, B. J. van Dam, C. P. “Effects of Compressibility on Design of Subsonic Natural Laminar Flow Fuselages,” AIAA Paper 86-1825 CP June 1987
- Dodbele, S. S. Holmes, B. J. van Dam, C. P. Vijgen, P. M. H. W. “Shaping of Airplane Fuselage for Minimum Drag,” Journal of Aircraft 24 5 May 1987 298 304
- Younghans, J. L. Lahti, D. J. “Experimental Studies on Natural Laminar Flow Nacelles,” AIAA Paper 84-0034 Jan. 1984
- Radespiel, R. Horstmann, K. Redeker, G. “Feasibility Study on the Design of a Laminar Flow Nacelle,” AIAA Paper 89-0640 Jan. 1989
- Malik, M. R. “Stability Theory for Laminar Flow-Control Design,” Progress in Astronautics and Aeronautics 123 1990
- Campbell, R. L. Smith, L. A. “A Hybrid Algorithm for Transonic Airfoil and Wing Design,” AIAA Paper 87-2552-cp Aug. 1987
- Chen, H. C. Yu, N. J. Rubbert, P. E. Jameson, A. “Flow Simulations for General Nacelle Configurations Using Euler Equations,” AIAA Paper 93-0539 1983
- Wie, Y. S. “A Three-Dimensional, Compressible, Boundary-Layer Method for General Fuselages,” I Numerical Method II User's Manual NASA CR-4292 May 1990
- Harris, J. E. Blanchard, D. K. “Computer Program for Solving Laminar, Transitional, or Turbulent Compressible Boundary-Layer Equations for Two-Dimensional and Axisymmetric Flow,” NASA TM 83207 Feb. 1982
- Malik, Mujeeb R. “ e Malik : A New Spatial Stability Analysis Program for Transition Prediction Using the e N Method,” High Technology Rept. HTC-8902 1989
- Arcara, P. C, Jr. Bartlett, D. W. McCullers, L. A. “Analysis for the Application of Hybrid Laminar-Flow Control to a Long-Range Subsonic Transport Aircraft,” SAE Paper No. 912113 1991