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Some Challenges in High-Alpha Vehicle Dynamics

  • L. E. Ericsson
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Summary

The evolution of aerospace vehicles towards ever-increasing maneuverability and agility, including flight at high angles of attack and vehicle motions of large amplitudes and high angular rates, has led to the need for prediction of vehicle aerodynamics that are dominated by unsteady separated flow effects. The existing data base is reviewed to determine to what degree the following critical issues are understood. 1. Cause and effect of asymmetric forebody flow separation with associated vortices. 2. Effect of asymmetry and breakdown of leading edge vortices, 3. Effect of vehicle motion on dynamic airfoil stall. The challenge is to extend the present knowledge to include the coupling existing between novel aerodynamic controls and the vehicle dynamics of agile aircraft operating at high angles of attack

Symbols

b

wing span

c

reference length, wing chord or diameter (d) for circular cylinder and body alone

d

cylinder diameter

f

frequency

k

dimensionless roll rate, k = ωb/2U,

1

sectional lift, coefficient cl = l /qc

rolling moment: coefficient C = ℓ /qS b

mp

sectional pitching moment, coefficient cm = mp/qc2

M

free stream Mach number

n

yawing moment, coefficient Cn = n/q Sb

p

roll rate

P

static pressure, coefficient Cp = (p-p)/q

q

dynamic pressure, q = pU 2/2

Re

Reynolds number, Re = Uc/v

S

reference area, = πd2/4 for body alone, = projected wing area for aircraft

t

time

UW

wall velocity

U

freestream velocity

x

axial distance from leading edge or body apex

Y

side force, coefficient CY = Y/qS

z

translatory coordinate

α

angle of attack

ā

effective angular amplitude

β

angle of sideslip

Δ

increment or amplitude

θ

purturbation in pitch

θA

apex half angle

θLE

complimentary angle to the leading edge sweep, θLE = n/2-A

Λ

leading edge sweep angle

ξ

dimensionless x-coordinate, ξ= x/c

ρ

air density

σ

inclination of roll axis

φ

roll angle

φ

dimensionless roll rate, φ= φb/2U

ψ

coning angle

v

kinematic viscosity

ω, ϖ

angular frequency, ω = 2nf, ϖ = ωC/U

A

apex

CG

enter of gravity or rotation center

LE

leading edge

LIM

limit cycle

s

separation

v

vortex

w

wake

W

wall

o

initial or time-average value

freestream condition

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References

  1. 1.
    Many authors, “Dynamic Stability Parameters”, AGARD CP-235, Nov. 1978.Google Scholar
  2. 2.
    Ericsson, L E., “Technical Evaluation Report on the Fluid Dynamics Panel Symposium on Dynamic Stability Parameters”, AGARD-AR-137, April 1979.Google Scholar
  3. 3.
    Ericsson, L. E, “A Summary of AGARD FDP Meeting on Dynamic Stability Parameters”, Paper 2, AGARD CP-260, May 1979.Google Scholar
  4. 4.
    Orlik-Rückemann, K. J., “Dynamic Stability Testing of Aircraft-Needs Versus Capabilities”, Progress Aerospace Sci., Pergamon Press. Vol. 16, No. 4, 1975, pp. 431–437.Google Scholar
  5. 5.
    Ericsson, L E., and Reding, J. P., “Review of Support Interference in Dynamic Tests” AIAA Journal, Vol. 21, No. 12, Dec. 1983, pp. 1652–1666.CrossRefGoogle Scholar
  6. 6.
    Ericsson, L E., and Reding, J. P., Dynamic Support Interference in High Alpha Testing,“ Journal of Aircraft, Vol. 23, Dec. 1986, pp. 889–896.Google Scholar
  7. 7.
    Ericsson, L. E., and Reding, J. P., “Scaling Problems in Dynamic Tests of Aircraft-Like Configurations”, Paper 25, AGARD CP-227, Feb. 1977.Google Scholar
  8. 8.
    Ericsson, L E., “Reflections Regarding Recent Rotary Rig Results”, Journal of Aircraft, Vol. 24, Jan. 1987, pp. 25–30.CrossRefGoogle Scholar
  9. 9.
    McElroy, G. E. and Sharp, P. S., “An Approach to Stall/Spin Development and Test”, AIAA Paper No. 71–772, July 1971.Google Scholar
  10. 10.
    Malcolm, G. N., Ng, T. T., Lewis, L C., and Murri, D. G., “Development of Non-Conventional Control Methods for High Angle of Attack blight Using Vortex Manipulation”, A1AA Paper 89–2192-CP, Aug. 1989.Google Scholar
  11. 11.
    Grafton, S. B., Chambers, J. R., and Coe, Jr., P. I_, “Wind-Tunnel Free-Flight Investigation of a Model of a Spin Resistant Fighter Configuration”, NASA TN D-7716, June 1974.Google Scholar
  12. 12.
    Ericsson, L E. and Reding, J. P., “Asymmetric Vortex Shedding from Bodies of Revolution”, Chapter VII, Tactical Missile Aerodynamics, Vol. 104, Progress Astro and Aero. Series, M. J., Hemsch and J. N. Nielson editors, (1986), pp. 243–296.Google Scholar
  13. 13.
    Lamont, P. and Kennaugh, A., “Multiple Solutions for Aircraft Sideslip Behavior at High Angles of Attack”, AIAA Paper 89–0645, Jan 1989.Google Scholar
  14. 14.
    Ericsson, L E., “Moving Wall Effects in Unsteady Flow”, Journal of Aircraft, Vol. 25, Nov. 1988, pp. 977–990.CrossRefGoogle Scholar
  15. 15.
    Atraghji, E. G., “The Influence of Mach Number, Semi-Nose Angle and Roll Rate on the Development of the Forces and Moments Over a Series of Long Slender Bodies of Revolution at Incidence” NAE Data Report 5x5/0020, (1967), National Research Council, Ottawa, Canada.Google Scholar
  16. 16.
    Yoshinaga, T., Tate, A., and Inoue, K., “Coning Motion of Slender Bodies at High Angles of Attack in Low Speed Flow”, AIAA Paper 81–1899, Aug. 1981.Google Scholar
  17. 17.
    Ericsson, L E, “Prediction of Slender Body Coning Characteristics”, Journal of Spacecraft and Rockets, Vol. 28, Jan.-Feb. 1991, pp. 43–49.Google Scholar
  18. 18.
    Swanson, W. M., “The Magnus Effect; A summary of Investigations to Date”, Journal of Basic Engineering, Vol. 83, Sept. 1961, pp. 461–470.CrossRefGoogle Scholar
  19. 19.
    Brandon, J. M. and Nguyen, L. T., “Experimental Study of Effects of Forebody Geometry on High Angle of Attack Static and Dynamic Stability”, Journal of Aircraft, Vol. 25, July 1988, pp. 591–597.CrossRefGoogle Scholar
  20. 20.
    Ericsson, L E., “Wing Rock Generated by Forebody Vortices”, Journal of Aircraft, Vol. 26, Feb. 1989, pp. 110–116.CrossRefGoogle Scholar
  21. 21.
    Ericsson, L E., “The Fluid Mechanics of Slender Wing Rock”, Journal of Aircraft, Vol. 21, May 1984, pp. 322–328.CrossRefGoogle Scholar
  22. 22.
    Ericsson, L. E., “Further Analysis of Wing Rock Generated by Forebody Vortices”, Journal of Aircraft, Vol. 26, Dec. 1989, pp. 1098–1104.CrossRefGoogle Scholar
  23. 23.
    Ericsson, L E., “Dynamic LEX/Forebody Vortex Interaction Effects”, AIAA Paper No. 92–2732, June 1992.Google Scholar
  24. 24.
    Malcolm, G. N., “Forebody Vortex Control”, Paper 6, AGARD-R-776, April 1991.Google Scholar
  25. 25.
    Ilebbar, S. K., Platzer, M. F., and Cavazos, O. V., “A Water Tunnel Investigation of the Effects of Pitch Rate and Yaw on LEX Generated Vortices of an F/A-18 Fighter Aircraft Model”, AIAA Paper No. 91–0280, Jan. 1991.Google Scholar
  26. 26.
    Cavazos, O. V. Jr., “A Flow Visualization Study of LEX Generated Vortices on a Scale Model of a F/A-18 Fighter Aircraft at high Angles of Attack”, M. S. Thesis, Naval Postgraduate School, Monterey, California, June 1990.Google Scholar
  27. 27.
    Nelson, R. C., “Unsteady Aerodynamics of Slender Wings”, Paper 1, AGARD-R-776, April 1991. (The F-18 wing rock results were only presented orally.)Google Scholar
  28. 28.
    Stahl, W., Mahmood, M. Asghar, A., “Experimental Investigation of the Vortex Flow on Very Slender Sharp-Edged Delta Wings at High Incidence”, Report 1B222–90A11, April 1990, DFLR, Gottingen, Germany.Google Scholar
  29. 29.
    Stahl, W. H., Mahmood, M., and Asghar, A.,“Experimental Investigations of the Vortex Flow on Delta Wings at High Incidence”, AIAA Journal, Vol. 30, April 1992, pp. 1027–1032.CrossRefGoogle Scholar
  30. 30.
    Nguyen, L E, Yip, L P., and Chambers, J. R., “Self Induced Wing Rock of Slender Delta Wings,” AIAA Paper 81–1883, Aug. 1981.Google Scholar
  31. 31.
    Ericsson, L E., “Slender Wing Rock Revisited”, AIAA Paper 91–0417, Jan 1991.Google Scholar
  32. 32.
    Ericsson, L. F.., “Analytic Prediction of the Maximum Amplitude of Slender Wing Rock,” Journal of Aircraft, Vol. 26, Jan 1989, pp. 35–39.CrossRefGoogle Scholar
  33. 33.
    Ng, T. T., Malcolm, G. N., and Lewis, L. C., “Experimental Study of Vortex Flows over Delta Wings in Wing-Rock Motion,” Journal of Aircraft, Vol. 29, July-Aug. 1992, pp. 598–603.Google Scholar
  34. 34.
    Ericsson, L E., and King, H. H. C., “Rapid Prediction of High-Alpha Unsteady Aerodynamics of Slender-Wing Aircraft”, Journal of Aircraft, Vol. 29, Jan.-Feb. 1991, PP. 85–92.Google Scholar
  35. 35.
    Arena, H. S. Jr., Nelson, R. C., and Schiff, LB., “An Experimental Study of the Nonlinear Dynamic Phenomenon known as Wing Rock”, AIAA Paper 90–2812-CP, Aug. 1990.Google Scholar
  36. 36.
    Ericsson, L E, “Various Sources of Wing Rock,” J. Aircraft, Vol. 27, June 1990, pp. 488–494.CrossRefGoogle Scholar
  37. 37.
    Keener, E. R. and Chapman, G. T., “Similarity in Vortex Asymmetries over Slender Bodies and Wings,” AIAA Journal, Vol. 15, No. 9, Sept 1977, pp. 1370–1372.CrossRefGoogle Scholar
  38. 38.
    Wendtz, W. II. and Koh’man, D. L, “Vortex Breakdown on Slender Sharp-Edged Wings”, AIAA Paper No. 69–778, July 1969.Google Scholar
  39. 39.
    Hanff, E. S. and Ericsson, L. E., “Multiple Roll Attractors of a Delta Wing at High Incidence”, Paper 31, AGARD - CP - 494, July 1991Google Scholar
  40. 40.
    Ericsson, L E. and Reding, J. P., “Fluid Mechanics of Dynamic Stall Part I. Unsteady Flow Concepts”, Journal of Fluids and Structures, Vol. 2, 1988, pp. 1–33.CrossRefGoogle Scholar
  41. 41.
    Iambourne, N. C., Bryer, D. W., and Maybrey, J. F. M., “Pressure Measurements on a Model Delta Wing Undergoing Oscillatory Deformation”, NPL Aero Report 1314, Aeronautical Research Council, Great Britain, March 1970.Google Scholar
  42. 42.
    Lambourne, N. C. and Bryer, D. W., “The Bursting of Leading-Edge Vortices - Some Observations and Discussion of the Phenomenon”, RandM No. 3282, Aeronautical Research Council, Great Britain, April 1961.Google Scholar
  43. 43.
    Ericsson, L. E. and Reding, J. P., “Approximate Nonlinear Slender Wing Aerodynamics,” Journal of Aircraft, Vol. 14, No. 12, Dec. 1977, pp. 1197–1204.CrossRefGoogle Scholar
  44. 44.
    Ericsson, L E. and Reding, J. P., “Unsteady Aerodynamic Analysis of Space Shuttle Vehicles. Part II: Steady and Unsteady Aerodynamics of Sharp-Edged Delta Wings”, NASA CR-120123, Aug. 1973.Google Scholar
  45. 45.
    Ericsson, L. E. and Ilanff, E. S., “Unique High-Alpha Roll Dynamics of a Sharp-Edged 65 deg. Delta Wing”, AIAA Paper No. 92–0276, Jan. 1992.Google Scholar
  46. 46.
    Carta, F. O., “A Comparison of the Pitching and Plunging Response of an Oscillating Airfoil”, NASA CR 3172, Oct. 1979.Google Scholar
  47. 47.
    Liu, 11.-T., “Unsteady Aerodynamics of a Wortmann Wing at Low Reynolds Numbers”, Journal of Aircraft, Vol. 29, No.3, May-June, 1992.Google Scholar
  48. 48.
    Maresca, C. A., Favier, D. J., Rebont, J. M., “Unsteady Aerodynamics of an Airfoil at High Angles of Incidence Performing Various linear Oscillations in a Uniform Stream”, Journal of the American 1-lelicopter Society, April 1981, pp. 40–45.Google Scholar
  49. 49.
    Carr, L W. McAlister, K. W., and McCroskey, W. J., “Analysis of Development of Dynamic Stall based on Oscillating Airfoil Experiments”, NASA TN D - 8382, 1977.Google Scholar
  50. 50.
    Ericsson, L E. and Reding, J. P., “The Difference Between the Effects of Pitch and Plunge on Dynamic Airfoil Stall”, Paper 8, Ninth European Rotorcraft Forum, Stresa, Italy, Sept. 13–15, 1983.Google Scholar
  51. 51.
    Ericsson, L E. and Reding, J. P., “Analytic Prediction of Dynamic Stall Characteristics”, AIAA Paper No. 72–682, June 1972.Google Scholar
  52. 52.
    Modi, V. J., Sun, J. L. C., Akutsu, T., Lake, P., McMillan, K., Swinton, P. G., and Mullins, D., “Moving Surface Boundary Layer Control for Aircraft Operation at Fligh Incidence”, AIAA Paper No. 80–11621, Aug. 1980.Google Scholar
  53. 53.
    Ericsson, L E., “Moving Wall Effects on Dynamic Stall can be Large-Fact or Fiction?” AIAA Paper No. 91–0430, Jan. 1991.Google Scholar
  54. 54.
    Ericsson, L. E., “Effects of Transition on Wind Tunnel Simulation of Vehicle Dynamics”, Progress in Aerospace Sciences, Vol. 27, 1990, pp. 121–144.CrossRefGoogle Scholar
  55. 55.
    Rainey, A. G., “Measurement of Aerodynamic Forces for Various Mean Angles of Attack on an Airfoil Oscillating in Bending with Emphasis on Damping in Stall”, NACA Tech Report 1305, 1957.Google Scholar
  56. 56.
    Jacobs, E. N. and Sherman, A., “Airfoil Section Characteristics as Affected by Variations in the Reynolds Number”, NACA Tech. Report 586, 1937Google Scholar
  57. 57.
    Liiva, J., “Unsteady Aerodynamic and Stall Effects on helicopter Rotor Blade Airfoil Sections”, J.urnal of Aircraft, Vol. 6, Jan.-Feb. 1969, pp. 46–51.Google Scholar
  58. 58.
    Fratello, D. J., Croom, M. A., Nguyen, L T., and Domack, C. S., “Use of the Updated NASA Langley Radio-Controlled Drop-Model Technique for High-Alpha Studies of the X-29A Configuration”, A1AA Paper No. 87–2559, Aug. 1987.Google Scholar
  59. 59.
    Ericsson, L E. and Reding, J. P., “Alleviation of Vortex-Induced Asymmetric Loads”, Journal of Spacecraft and Rockets, Vol. 17, Nov.-Dec., 1980, pp. 548–553.Google Scholar
  60. 60.
    Ericsson, L E., “Control of Forebody Flow Asymmetry, a Critical Review”, AIAA Paper 90–2833, Aug. 1990.Google Scholar
  61. 61.
    Ilerbst, W. B., “Future Fighter Technologies”, Journal of Aircraft, Vol. 17, Aug. 980, pp. 561–566.Google Scholar
  62. 62.
    Herbst, W. B., “Supermaneuverahility”, Proceedings of Workshop on Unsteady Separated Flow, Aug. 11, 1983, Frances and Luttges editors (1984), pp. 1–9.Google Scholar
  63. 63.
    Ng, T. T., Ong, L Y., Suarez, C. J., and Malcolm, G. N., “Wing Rock Suppression Using Forebody Vortex Control”, AIAA Paper No. 91–3227-CP, Sept. 1991.Google Scholar
  64. 64.
    Dobbs, S. K., Miller, G. D., and Stevenson, J. R., “Self-Induced Oscillation Wind Tunnel Test of a Variable Sweep Wing”, AIAA Paper 85–0739, April 1985.Google Scholar
  65. 65.
    Ericsson, L E, “Vortex-Induced Bending Oscillation of a Swept Wing”, Journal of Aircraft, Vol. 24, March 1987, pp. 195–202.CrossRefGoogle Scholar
  66. 66.
    Bergmann, B., Hummel, D., and Oelker, H.-Chr., “Vortex Formation over a Close-Coupled Canard-Wing-Body Configuration in Unsymmetric Flow”, Paper 14, AGARD-CP-494, July 1991.Google Scholar
  67. 67.
    Freymuth, Peter, “Three-Dimensional Vortex Systems of Finate Wings”, Journal of Aircraft, Vol. 25, Oct. 1988, pp. 971–972.CrossRefGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1993

Authors and Affiliations

  • L. E. Ericsson
    • 1
  1. 1.Lockheed Missiles & Space Company, Inc.SunnyvaleUSA

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