The Langley 8-ft Transonic Pressure Tunnel Laminar-Flow-Control Experiment

Background and Accomplishments
  • Percy J. Bobbitt
  • William D. Harvey
  • Charles D. Harris
  • Cuyler W. BrooksJr.
Part of the ICASE/NASA LaRC Series book series (ICASE/NASA)

Abstract

The NASA’s response to the oil shortage and price increases of the 70’s was the creation of the Aircraft Energy Efficiency (ACEE) Program. Its objective was to provide aerodynamic and controls technology that would enable the design of commercial transports with substantially better fuel efficiency than those in service at the time. This program had a number of facets, most of which were centered on supercritical airfoil/wing and winglet technology, and included both industry and NASA in-house research components. This paper concerns one of the NASA in-house activities, the Langley Laminar Flow Control (LFC) Project, which was carried out in the Langley 8-foot Transonic Pressure Tunnel (8-ft TPT). The idea for such an undertaking came from Dr. Werner Pfenninger in 1975 and stemmed, primarily, from a desire to know more about the compatability of a high performance supercritical wing with laminar flow control. The possible adverse effect of a large supersonic zone and its associated wave structure on the stability of a suction controlled boundary layer was a particular concern.

Keywords

Vortex Manifold Foam Ozone Milling 

Abbreviations

ACEE

NASA’ Aircraft Energy Efficiency Program

ARC

NASA Ames Research Center

ATM

atmospheric pressure, 14.7 psi

CF

crossflow

HLFC

hybrid laminar flow control

Hz

Hertz

LE

leading edge

LFC

laminar flow control

LRC

NASA Langley Research Center

LTPT

NASA Langley Low Turbulence Pressure Tunnel

RSL

reference suction level ( = CQ/CQref)

TE

trailing edge

TS

Tollmien-Schlichting

8-ft TPT

NASA Langley 8-ft Transonic Pressure Tunnel

12-ft PT

NASA Ames 12-ft Pressure Tunnel

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References

  1. [1]
    Bobbitt, P. J.; Waggoner, E. G.; Harvey, W. D.; and Dagenhart, J. It.: A Faster “Transition” to Laminar Flow. SAE 851855, Aerospace Technology Conference and Exposition, Anaheim, CA, October 1988.Google Scholar
  2. [2]
    Lachmann, G. V. ed.: Boundary Layer and Flow Control, Volume 2. Pergamon Press, 1961.MATHGoogle Scholar
  3. [3]
    Wagner, R.; Maddalon, D. V.; Bartlett, D. W.; Collier, F. S., Jr.; and Braslow, A. L.: Laminar Flow Flight Experiments — A Review. Natural Laminar Flow and Laminar Flow Control, M. Y. Hussaini and R. W. Barnwell (editors ), Springer-Verlag, 1991.Google Scholar
  4. [4]
    Pfenninger, Werner: Laminar Flow Control Laminarization. Special Course on Concepts for Drag Reduction, AGARD-R-654, June 1977, pp. 3–1 to 3–75.Google Scholar
  5. [5]
    Pfenninger, W.; and Groth, E.: Low Drag Boundary Layer Suction Experiments in Flight on a Wing Glove of an F-94A Airplane with Suction through a Large Number of Fine Slots. Boundary Layer and Flow Control, Volume 2, G. V. Lachman, ed., Pergamon Press, 1961, pp. 981–999.Google Scholar
  6. [6]
    Fowell, L. R.; and Antonatos, P. P.: Laminar Flow Control Flight Test Results, Some Results from the X-21A Program. Recent Developments in Boundary Layer Research, Part IV, May 1965. AGARDograph 97, pp. 1–76.Google Scholar
  7. [7]
    Lumley, J. L.: Passage of a Turbulent Stream through Honeycomb of Large Length-to-Diameter Ratio. Trans. ASME, Ser. D: J. Basic Eng., Vol. 86, No. 2, June 1964, pp. 218–220.Google Scholar
  8. [8]
    Loehrke, R. I.; and Nagib, H. M.: Control of Free-Stream Turbulence by Means of Honeycombs: A Balance between Suppression and Generation. J. Fluids Eng., Vol. 98, Ser. I, No. 3, September 1976, pp. 342–353.CrossRefGoogle Scholar
  9. [9]
    Prandtl, L.: Attaining a Steady Air Stream in Wind Tunnels. NACA TM 726, 1933.Google Scholar
  10. [10]
    Schubauer, G. B.; Spangenberg, W. G.; and Klebanoff, P. S.: Aerodynamic Characteristics of Damping Screens. NACA TN 2001, 1950.Google Scholar
  11. [11]
    Dryden, Hugh L.; and Schubauer, G. B.: The Use of Damping Screens for the Reduction of Wind-Tunnel Turbulence. J. Aeronaut. Sci., Vol. 14, No. 4, Apr. 1947, pp. 221–228.Google Scholar
  12. [12]
    Collar, A. R.: The Effect of a Gauze on the Velocity Distribution in a Uniform Duct. R. & M. No. 1867, British A.R.C., 1939.Google Scholar
  13. [13]
    Taylor, G. I.; and Batchelor, G. K.: The Effect of Wire Gauze on Small Disturbances in a Uniform Stream. Q. J. Mech. & Appl. Math., Vol. 2, Pt. 1, March 1949, pp. 1–29.MathSciNetMATHCrossRefGoogle Scholar
  14. [14]
    Harvey, William D.; Stainback, P. Calvin; and Owen, F. Kevin: Evaluation of Flow Quality in Two Large NASA Wind Tunnels at Transonic Speeds. NASA TP-1737, 1980.Google Scholar
  15. [15]
    Owen, F. K.; Stainback, P. Calvin; and Harvey, William D.: An Evaluation of Factors Affecting the Flow Quality in Wind Tunnels. AGARD-CP-348, Wind Tunnels and Testing Techniques, pp. 12–17, 12–22.Google Scholar
  16. [16]
    Scheiman, James; and Brooks, J. D.: A Comparison of Experimental and Theoretical Turbulence Reduction from Screens, Honeycomb and Honeycomb-Screen Combinations. A Collection of Technical Papers — AIAA 11th Aerodynamic Testing Conference, American Inst. of Aeronautics and Astronautics, 1980, pp. 129–137. (Available as AIAA-80–0433.)Google Scholar
  17. [17]
    McKinney, Marion O.; and Scheiman, James: Evaluation of Turbulence Reduction Devices for the Langley 8-Foot Transonic Pressure Tunnel NASA TM-81792, 1981.Google Scholar
  18. [18]
    Scheiman, James: Considerations for the Installation of Honeycomb and Screens to Reduce Wind-Tunnel Turbulence. NASA TM-81868, 1981.Google Scholar
  19. [19]
    Stainback, P. C.; Johnson, C. B.; and Basnett, C. B.: Preliminary Measurements of Velocity, Density, and Total Temperature Fluctuations in Compressible Subsonic Flow. AIAA 21st Aerospace Sciences Meeting, January 1983.Google Scholar
  20. [20]
    Stainback, P. C.: A Review of Hot-Wire Anemometry in Transonic Flows. ICIASF ‘85, pp. 67–78, Stanford, CA, August 1985.Google Scholar
  21. [21]
    Bobbitt, P. J.: Instrumentation Advances for Transonic Testing. Transonic Symposium: Theory, Application, and Experiment, NASA Langley Research Center, Hampton, VA, April 19–21, 1988, Jerome T. Foughner, Jr. (Compiler), NASA CP-3020, Vol. I, Part 2.Google Scholar
  22. [22]
    Jones, G. S.; Stainback, P. C.; Harris, C. D.; Brooks, C. W.; and Clukey, S. J.: Flow Quality Measurements for the Langley 8-Foot Transonic Pressure Tunnel LFC Experiment. 27th Aerospace Sciences Meeting, Reno, NV, January 9–12, 1989, AIAA Paper No. 89–0150.Google Scholar
  23. [23]
    Jones, G. S.; and Stainback, P. C.: A New Look at Wind Tunnel Flow Quality for Transonic Flows. SAE 881452 Aerospace Technology Conference and Exposition, Anaheim, CA, October 1988.Google Scholar
  24. [24]
    Bauer, F.; Garabedian, P.; and Korn, D.: A Theory of Supercritical Wing Sections, With Computer Programs and Examples. Volume 66 of Lecture Notes in Economics and Mathematical Systems, Springer-Verlag, 1972.Google Scholar
  25. [25]
    Bauer, Frances; Garabedian, Paul; Korn, David; and Jameson, Antony: Supercritical Wing Sections II. Volume 108 of Lecture Notes in Economics and Mathematical Systems, Springer-Verlag, 1975.Google Scholar
  26. [26]
    Harris, Charles D.: Aerodynamic Characteristic of a 14-PercentThick NASA Supercritical Airfoil Designed for a Normal-Force Coefficient of 0.7. NASA TM X-72712, 1975.Google Scholar
  27. [27]
    Allison, D. O.; and Dagenhart, J. R.: Design of a LaminarFlow-Control Supercritical Airfoil for a Swept Wing. CTOL Transport Technology-1978, NASA CP-2036, Part 1, 1978, pp. 395–408.Google Scholar
  28. [28]
    Allison, D. O.: Inviscid Analysis of Two Supercritical LaminarFlow-Control Airfoils at Design and Off-Design Conditions. NASA TM-84657, 1983.Google Scholar
  29. [29]
    Allison, D. O.; and Dagenhart, J. R.: Two Experimental Supercritical Laminar-Flow-Control Swept-Wing Airfoils. NASA TM-89073, February 1987.Google Scholar
  30. [30]
    Pfenninger, W.; Reed, Helen L.; and Dagenhart, J. R.: Design Considerations of Advanced Supercritical Low-Drag Suction Airfoils. Viscous Flow Drag Reduction, Gary R. Hough, ed., AIAA, c. 1980, pp. 249–271.Google Scholar
  31. [31]
    Van Ingen, J. L.; Blom, J. J. H.; and Goei, J. H.: Design Studies of Thick Laminar Flow Airfoils for Low-Speed Flight Employing Turbulent Boundary-Layer Suction over the Rear Part. AGARD CP-365, May 1984.Google Scholar
  32. [32]
    Klebanoff, P. S.; and Tidstrom, K. D.: Evolution of Amplified Waves Leading to Transition in a Boundary Layer with Zero Pressure Gradient. NASA TN D-195, 1958.Google Scholar
  33. [33]
    Dagenhart, J. R.: Amplified Crossflow Disturbances in the Laminar Boundary Layer on Swept Wings with Suction. NASA TP1902, 1981.Google Scholar
  34. [34]
    Srokowski, A. J.; and Orszag, S. A.: Mass Flow Requirements for LFC Wing Design. AIAA Paper 77–1222, August 1977.Google Scholar
  35. [35]
    Mack, L. M.: Transition Prediction and Linear Stability Theory. AGARD CP-224, January 1970.Google Scholar
  36. [36]
    Malik, M. R.; and Orszag, S. A.: Efficient Computation of the Stability of Three-Dimensional Compressible Boundary Layers. AIAA Paper 81–1277, June 1981.Google Scholar
  37. [37]
    El Hady, N. M.: On the Stability of Three-Dimensional Compressible Nonparallel Boundary Layers. AIAA 80–1374, July 1980.Google Scholar
  38. [38]
    Reed, H. L.; and Nayfeh, A. H.: Stability of Compressible Three-Dimensional Boundary-Layer Flows. AIAA 82–1009, June 1982.Google Scholar
  39. [39]
    Reed, H. L.: Wave Interactions in Swept Wing Flows. Phys. Fluids, Vol. 30, 1987.Google Scholar
  40. [40]
    El Hady, N. M.: Evolution of Resonant Wave Triads in Three-Dimensional Boundary Layers. Phys. Fluids, March 1989.Google Scholar
  41. [41]
    Nayfeh, A. H.: Effect of Streamwise Vortices on TollmienSchlichting Waves. Journal of Fluid Mechanics, Vol. 107, 1981, p. 441.ADSMATHCrossRefGoogle Scholar
  42. [42]
    Nayfeh, A. H.: Influence of Görtler Vortices on TollmienSchlichting Waves. AIAA PPer 87–1206, 1987.Google Scholar
  43. [43]
    Malik, M. R.: Wave Interaction in Three-Dimensional Boundary Layers. AIAA Paper 86–1129, 1980.Google Scholar
  44. [44]
    Herbert, T.; and Morkovin, M. V.: Dialogue on Bridging Some Gaps in Stability and Transition Research. Laminar-Turbulent Transition, R. Eppler and H. Fasel, eds., Springer-Verlag, 1980.Google Scholar
  45. [45]
    Saric, W. S.; and Reed, H. L.: Three-Dimensional Stability of Boundary Layers. Proceeding Perspectives in Turbulence Symposium, Göttingen, West Germany, May 11–15, 1987.Google Scholar
  46. [46]
    Morkovin, M. V.: On the Many Faces of Transition Viscous Drag Reduction. C. S. Wells, ed., Plenum Publ., 1969.Google Scholar
  47. [47]
    Kaups, K.; and Cebeci, T.:, Compressible Laminar Boundary Layers with Suction on Swept and Tapered Wings. J. Aircraft, Vol. 14, No. 7, July 1977, pp. 661–667.CrossRefGoogle Scholar
  48. [48]
    Mack, L. M.: On the Stability of the Boundary Layer on a Transonic Swept Wing. AIAA 79–0264, January 1979.Google Scholar
  49. [49]
    Pfenninger, W.: Special Course on Concepts for Drag Reduction, Chapter 3 - Laminar Flow Control, Laminarization. AGARD Report 654, June 1977.Google Scholar
  50. [50]
    Smith, A. M. O.; and Gameroni, N.: Transition, Pressure Gradient, and Stability Theory. Proc. Int. Congress Appl. Mech., 9, Brussels, Vol. 4, 1956.Google Scholar
  51. [51]
    Van Ingen, J. L.: A Suggested Semi-Empirical Method for the Calculation of the Boundary-Layer Transition Region. Report No. VTH 71, VTH 74, Delft, Holland, 1956.Google Scholar
  52. [52]
    Hefner, J. N.; and Bushnell, D. M.: Application of Stability Theory to Laminar Flow Control. AIAA Paper 79–1493, July 1979.Google Scholar
  53. [53]
    Smith, A. M. O.: On Growth of Taylor-Görtler Vortices Along Highly Concave Walls. Q. Appl. Math., Vol. XIII, No. 3, Oct. 1955, pp. 233–262.Google Scholar
  54. [54]
    El-Hady, Nabil M.; and Verma, Alok K.: Growth of Görtler Vortices in Compressible Boundary Layers Along Curved Surfaces. AIAA-81–1278, June 1981.Google Scholar
  55. [55]
    Kobayashi, R.: Taylor-Görtler Instablity of a Boundary Layer with Suction or Blowing. Rep. No. 289, Inst. of High Speed Mechanics, Tohoku Univ., Vol. 32, 1975, pp. 129–148.Google Scholar
  56. [56]
    Pfenninger, W.; and Syberg, J.: Reduction of Acoustic Disturbances in the Test Section of Supersonic Wind Tunnels by Laminarizing Their Nozzles and Test Section Wall Boundary Layers by Means of Suction. NASA CR-2436, 1974.Google Scholar
  57. [57]
    Carlson, Leland A.: TRANDES: A FORTRAN Program for Transonic Airfoil Analysis or Design. NASA CR-2821, 1977.Google Scholar
  58. [58]
    Newman, Perry A.; Anderson, E. Clay; and Peterson, John B., Jr.: Aerodynamic Design of the Contoured Wind-Tunnel Lever for the NASA Supercritical, Laminar-Flow-Control, Swept-Wing Experiment. NASA TP-2335, September 1984.Google Scholar
  59. [59]
    Carmichael, B. H.: Surface Waviness Criteria for Swept and Unswept Laminar Suction Wings. Rep. No. NOR-59–438 (BLC123) Contract AF33(616)-3168), Northrop Aircraft, Inc., August 1959.Google Scholar
  60. [60]
    Carmichael, B. H.; and Pfenninger, W.: Surface Imperfection Experiments on a Swept Laminar Suction Wing. Rep. No. NOR-59–454 (BLC-124), Northrop Corp., August 1959.Google Scholar
  61. [61]
    Pfenninger, W.; Bacon, J.; and Goldsmith, J.: Flow Disturbances Induced by Low-Drag Boundary-Layer Suction through Slots. Phys. Fluids Suppl., Vol. 10, No. 9, Pt. II, September 1967, pp. S112–5114.Google Scholar
  62. [62]
    Harris, Charles D.; Harvey, William D.; and Brooks, Cuyler W., Jr.: The NASA Langley Laminar-Flow-Control Experiment on a Swept, Supercritical Airfoil, Design Overview, NASA TP-2809, May, 1988.Google Scholar
  63. [63]
    Maddalon, Dal V.; and Poppen, William A., Jr.: Design and Fabrication of Large Suction Panels with Perforated Surfaces for Laminar Flow Control Testing in a Transonic Wind Tunnel. NASA TM-89011, 1986.Google Scholar
  64. [64]
    Harris, C. D.; and Brooks, C. W., Jr.: Modifications to the Langley 8-Foot Transonic Pressure Tunnel for the Laminar Flow Control Experiment. NASA TM-4032, 1988.Google Scholar
  65. [65]
    Newman, P. A.; Kemp, W. B.; and Garriz, J. A.: Wall Interference Assessment and Correlations. Transonic Symposium: Theory, Application, and Experiment. NASA CP-3020, Vol. I and I I, April 1988.Google Scholar
  66. [66]
    Harris, C. D.; Brooks, C. W., Jr.; Stack, J. P.; and Clukey, P. G.: The NASA Langley Laminar-Flow-Control Experiment on a Swept Supercritical Airfoil - Basic Results for Slotted Configuration. NASA TM-4100, June 1989.Google Scholar
  67. [67]
    Brooks, C. W., Jr.; Harris, C. D.; and Harvey, W. D.: The NASA Langley Laminar-Flow-Control Experiment on a Swept Supercritical Airfoil — Drag Equations. NASA TM-4096, February 1989.Google Scholar
  68. [68]
    Berry, S. A.: Incompressible Boundary-Layer Stability Analysis of LFC Experimental Data for Sub-Critical Mach Numbers. NASA CR-3999, July 1986.Google Scholar
  69. [69]
    Brooks, C. W., Jr.; and Harris, C. D.: Results of LFC Experiment on Slotted Swept Supercritical Airfoil in Langley’s 8-Foot Transonic Pressure Tunnel. NASA CP-2487, Part 2, May 1987.Google Scholar
  70. [70]
    Berry, S. A.; Dagenhart, J. R.; Brooks, C. W., Jr.; and Harris, C. D.: Boundary-Layer Stability Analysis of LaRC 8-Foot LFC Experimental Data. NASA CP-2487, Part 2, March 1987.Google Scholar
  71. [71]
    Harvey, W. D.; Harris, C. D.; Sewall, W. G.; and Stack, J. P.: Laminar Flow Wind Tunnel Experiments. NASA CP-3020, Vol. I and I I, April 1988.Google Scholar
  72. [72]
    Berry, S. A.; Dagenhart, J. R.; Viken, J. K.; and Yeaton, R. B.: Boundary-Layer Stability Analysis of NLF and LFC Experimental Data at Subsonic and Transonic Speeds. SAE TP-871859, October 1987.Google Scholar
  73. [73]
    Vijgen, P. M. H. W.; Dodbele, S. S.; Pfenninger, W.; and Holmes, B. T.: Analysis of Wind Tunnel Boundary-Layer Transition Experiments on Axisymmetric Bodies at Transonic Speeds Using Compressible Boundary-Layer Stability Theory. AIAA 88–0008, January 1988.Google Scholar
  74. [74]
    Croom, C. C.; Manuel, G. S.; and Stack, J. P.: In-Flight Detection of Tollmien-Schlichting Instabilities in Laminar Flow. SAE Paper 871016, April 1987.Google Scholar
  75. Boeing Commercial Airplane Company: Flight Survey of the 757 Wing Noise Field and Its Effects on Laminar Boundary Layer Transition. Vols. I and II. NASA CR-178216.Google Scholar
  76. [76]
    Rozendaal, R. A.: Natural Laminar Flow Flight Experiments on a Swept Wing Business Jet - Boundary Layer Stability Analysis. NASA CR-3975, May 1986.Google Scholar
  77. [77]
    Rozendaal, R. A.: Variable-Sweep Transition Flight Experiment ( VSTFE) Stability Code Development and Clean-Up Glove Data Analysis. NASA CP- 2487, March 1987.Google Scholar
  78. [78]
    Befus, J.; Nelson, R.; Latos, J., Sr.; and Ellis, D.: Flight Test Investigations of a Wing Designed for Natural Laminar Flow. SAE TP-871044, April 1982.Google Scholar
  79. [79]
    Runyan, L. J.; Navran, B. H.; and Rozendaal, R. A.: F-111 Natural Laminar Flow Glove Flight Test Data Analysis and Boundary-Layer Stability Analysis. NASA CR-166051, 1984.Google Scholar
  80. [80]
    Runyan, L. J.: Boundary Layer Stability Analysis of a Natural Laminar Flow Glove on the F-111 Tact Airplane. Symposium on Viscous Drag Reduction, Dallas, Texas, November 7–8, 1979.Google Scholar
  81. [81]
    Fisher, D. F.; and Dougherty, N. S.: In Flight Transition Measurements on a 10 Degree Cone at Mach Numbers Form 0.5 to 2.0. NASA TP-1971, June 1982.Google Scholar
  82. [82]
    Mack, L. M.: Progress in Compressible Boundary-Layer Stability Computations. Proceedings of the Boundary-Layer Transition Workshop, Vol. IV, Rept. No. TOR-0172(52816–16)-5, December 1971.Google Scholar
  83. [83]
    Johnson, Charles, B.; Carraway, Debra L.; Hopson, Purnell, Jr.; and Tran, Sang Q.: Status of a Specialized Boundary Layer Transition Detection System for Use in the U.S. National Transonic Facility. Presented at the 12th International Congress on Instrumentation in Aerospace Simulation Facilities, Williamsburg, Virginia, June 22–25, 1987.Google Scholar
  84. [84]
    Stack, J. P.; Mangalam, S. M.; and Berry, S. A.; A Unique Measurement Technique to Study Laminar-Separation Bubble Characteristics on an Airfoil. AIAA Paper 87–1271, June 1987.Google Scholar
  85. [85]
    Goradia, S. H.; Bobbitt, P. J.; and Harvey, W. D.: Computational Results for the Effects of External Disturbances on Transition Location on Bodies of Revolution from Subsonic to Supersonic Speeds and Comparisons with Experimental Data. Aerospace Technology Conference and Exposition, Anaheim, CA, September 25–28, 1989, SAE Technical Paper Series 892381.Google Scholar
  86. [86]
    Kalburgi, Vijay; Mangalam, S. M.; Dagenhart, J. R.; and Tiwari, S. N.: Görtler Instability on an Airfoil. Proceedings of Conference on “Research in Natural Laminar-Flow Control,” NASA CP2487, Part 1, 1987.Google Scholar
  87. [87]
    Goradia, S. H.; Bobbitt, P. J.; Morgan, H. L.; Ferris, J. C.; and Harvey, W. D.: Results of Correlations for Transition Location on a Clean-Up Glove Installed on an F-14 Aircraft and Design Studies for a Laminar Glove for the X-29 Aircraft Accounting for Spanwise Pressure Gradient. Proceedings of a “Transonic Symposium” held at NASA Langley Research Center, NASA CP-3020, Vol. II, April 19–21, 1988.Google Scholar
  88. [88]
    Bobbitt, Percy J.: Transition Research Opportunities at Subsonic and Transonic Speeds. Instability, and Transition Proceedings. NASA Langley Research Center, May 15 - June 19, 1989, Robert G. Voigt and M. Y. Hussaini (eds. ), Springer-Verlag.Google Scholar

Copyright information

© Springer-Verlag New York, Inc. 1992

Authors and Affiliations

  • Percy J. Bobbitt
    • 1
  • William D. Harvey
    • 1
  • Charles D. Harris
    • 1
  • Cuyler W. BrooksJr.
    • 1
  1. 1.Langley Research CenterHamptonUSA

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