Hostname: page-component-7479d7b7d-fwgfc Total loading time: 0 Render date: 2024-07-15T08:43:14.787Z Has data issue: false hasContentIssue false
  • English
  • Français

Flow Separation and Stall Characteristics of Plane, Constant-Section Wings in Subcritical Flow

Published online by Cambridge University Press:  04 July 2016

P. D. Chappell
P. D. Chappell*
Affiliation:
Engineering Sciences Data Unit, Royal Aeronautical Society
Get access Rights & Permissions [Opens in a new window]

Summary

This paper discusses the various aspects of flow separation on wings and aerofoils at subcritical Mach numbers. It is shown that in general the onset of non-linearities in the aerodynamic characteristics, for plane constant-section wings, can be related to the initiation of regions of flow separation somewhere on the wing and often near the wing tip.

Empirical correlations are produced, tor plane wings of constant symmetrical section, enabling estimates to be made of the lift coefficient for onset of separation at either the leading or trailing edge of the wing.

A correlation of stall types on aerofoils, due to Gault, is extended in application to the estimation of initial stall and separation types for plane wings of constant symmetrical section. Suggestions for extending the application of this correlation to the estimation of section stall type for cambered, twisted and non-constant section wings are made.

Type
Supplementary Papers
Information
The Aeronautical Journal , Volume 72 , Issue 685 , January 1968 , pp. 82 - 90
Copyright
Copyright © Royal Aeronautical Society 1968 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Gaster, M. The Structure and Behaviour of Laminar Separation Bubbles. Separated Flows, Part II. AGARD Conference Proceedings, No 4, May 1966.Google Scholar
2. Gault, D. E. A Correlation of Low-Speed Airfoil-Section Stalling Characteristics with Reynolds Number and Air foil Geometry. NACA TN 3963, 1957. 1.Google Scholar
3. Wetzel, B. E. Effect of Taper Ratio on Lift, Drag, and Pitching-Moment Characteristics of Thin Wings of Aspect Ratio 3 with 53.1° Sweepback of Leading-Edge at Sub sonic and Supersonic Speeds. NACA RM A54J20 (TIL 4535), 1954.Google Scholar
4. Arabian, D. D. Investigation at Transonic Speeds of Loading over a 30° Swept Back Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a body. NASA TN D-421, 1957.Google Scholar
5. Brebner, G. G. and Wyatt, L. A. Boundary Layer Mea surements at Low Speed on Two Wings of 45° and 55° Sweep. RAE TN Aero 2702, 1960.Google Scholar
6. Garner, H. C. and Walshe, D. E. Pressure Distribution and Surface Flow on 5% and 9% Thick Wings with Curved Tip and 60° Sweepback. ARC R and M 3244, 1960.Google Scholar
7. Rogers, E. W. E., Berry, C. J. and Townsend, J. E. G. A Study of the Effect of Leading-Edge Modifications on the Flow Over a 50° Sweptback Wing at Transonic Speeds. ARC R and M 3270, 1960.Google Scholar
8. Demele, F. A. and Harmon Powell, K. The Effects of an Inverse Taper Leading-Edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-Body Combination Having an Aspect Ratio of 3 and 45° of Sweepback at Mach Numbers to 0.92. NACA TN 4366, 1958.Google Scholar
9. Hall, I. M. and Rogers, E. W. E. The Flow Pattern on a Tapered Sweptback Wing at Mach Numbers Between 0.6 and 1.6. ARC R and M 3271 (Part 1), 1960.Google Scholar
10. Sutton, E. P. Some Observations on the Flow Over a Delta-Winged Model With 55° Leading-Edge Sweep, at Mach Numbers Between 0.4 and 1.8. ARC R and M 3190, 1955.Google Scholar
11. Rogers, E. W. E., Hall, I. M. and Berry, C. J. An Investigation of the Flow About a Plane Half-Wing of Cropped-Delta Planform and 6% Symmetrical Section at Stream Mach Numbers Between 0.8 and 1.41. ARC 22 191, 1960.Google Scholar
12. Lipson, S. and Reed Barnett, U. Force and Pressure Investigation at Large-Scale of a 49° Sweptback SemispanWing Having NACA 65A006 Sections and Equipped With Various Slat Arrangements. NACA RM L51K26 (TIL 3001), 1951.Google Scholar
13. McCormack, G. M. and Walling, W. C. Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63°—Investigation of a Large-Scale Model at Low Speed. NACA RM A8D02 (TIL 2064), 1948.Google Scholar
14. Cahill, J. F. and Gottlieb, S. M. LOW Speed Aero dynamic Characteristics of a Series of Swept Wings Having NACA 65A006 Airfoil Sections. NACA RM L50F16 (TIL 2555), 1950.Google Scholar
15. McCullough, G. B. The Effect of Reynolds Number on the Stalling Characteristics and Pressure Distributions of Four Moderately Thin Airfoil Sections. NACA TN 3524, 1955.Google Scholar
16. McCullough, G. B. and Gault, D. E. Examples of Three Representative Types of Airfoil-Section Stall at Low Speed. NACA TN 2502, 1951.Google Scholar
17. Thwaites, B. Incompressible Aerodynamics, p 521. Oxford University Press, 1960.Google Scholar
18. Haines, A. B. and Rhodes, C. W. Tests in the Royal Aircraft Establishment 10 ft X 7 ft High Speed Tunnel on 50° Sweptback Wings. ARC R and M 3043 (Part 1), 1954.Google Scholar
19. Kolbe, C. D. and Boltz, F. W. The Forces and Pressure Distribution at Subsonic Speeds on a Plane Wing Having 45° of Sweepback, an Aspect-Ratio of 3, and a Taper Ratio of 0.5. NACA RM A51G31 (TIL 2894), 1951.Google Scholar
20. Walker, H. J. and Maillard, W. C. A Correlation of Airfoil Section Data with the Aerodynamic Loads Mea sured on a 45° Sweptback Wing Model at Subsonic Mach Numbers. NACA RM A55C08 (TIL 4684), 1955.Google Scholar
21. Garner, H. C. and Cox, D. K. Surface Oil-Flow Patterns on Wings of Different Leading-Edge Radius and Sweep- back. ARCCP 583, 1961.Google Scholar
22. Bird, J. D., Lichtenstein, J. H. and Jaquet, B. M. In vestigation of the Influence of Fuselage and Tail Surfaces on Low-Speed Static Stability and Rolling Characteristics of a Swept Wing Model. NACA TN 2741, 1947.Google Scholar
23. Goodman, A. and Brewer, J. D. Investigation at Low Speeds of the Effect of Aspect Ratio and Sweep on Static : and Yawing Stability Derivatives of Untapered Wings. NACATN 1669, 1948.Google Scholar
24. Black, J. Pressure Distribution and Boundary Layer In vestigations on 44° Sweptback Tapered Wing. ARC CP 137, 1952.Google Scholar
25. Garner, H. C. and Bryer, D. W. Experimental Study of Surface Flow and Part-Span Vortex Layers on a Cropped Arrowhead Wing. ARC R and M 3107, 1957.Google Scholar
26. Jones, M. R., Miles, C. J. W. and Pusey, P. S. Experiments in the Compressed Air Tunnel on Sweptback Wings Including Two Delta Wings. ARC R and M 2871, 1948.Google Scholar
27. Page Hoggard, H. and Hagerman, J. R. Downwash and Wake Behind Untapered Wings of Various Aspect Ratios and Angles of Sweep. NACA TN 1703, 1948.Google Scholar
28. Graham, R. R. Low-Speed Characteristics of a 45° Swept back Wing of Aspect Ratio 8 from Pressure Distributions and Force Tests at Reynolds Numbers from 1.5X106 to 4.8X106. NACA RM L51H13 (TIL 2920), 1951.Google Scholar
29. Tinling, B. E. and Lopez, A. E. The Effects of Reynolds Numbers at High Mach Numbers up to 0.94 on the Loading on a 35° Sweptback Wing Having. NACA 65iA012 Streamwise Sections. NACA RM A52B20 (TIL 3189), 1952.Google Scholar
30. Küchemann, D., Weber, J. and Brebner, G. G. Low-Speed Tests on 45° Sweptback Wings. ARC R and M 2882 (Part II), 1951.Google Scholar
31. Tinling, B. E. and Kolk, W. R. The Effects of Mach Number and Reynolds Number on the Aerodynamic Characteristics of Several 12% Thick Wings Having 35° of Sweepback and Various Amounts of Camber. NACA RM A50K27 (TIL 2629), 1950.Google Scholar
32. Abbott, I. H. and Von Doenhoff, A. E. Theory of Wing Sections. McGraw-Hill, 1949.Google Scholar
33. Loftin, L. K. and Smith, H. A. Aerodynamic Characteristics of 15 NACA Airfoil Sections at Seven Reynolds Numbers from 0.7X106 to 90X106. NACA TN 1945, 1949.Google Scholar
34. Nash, J. F., Moulden, T. H. and Osborne, J. On the Variation of Profile Drag Coefficient Below the Critical Mach Number. ARC CP 758, 1963.Google Scholar
35. Furlong, G. C. and Mchugh, J. G. A Summary and Analysis of the Low-Speed Longitudinal Characteristics of Swept Wings at High Reynolds Number. NACA Report 1339, 1952.Google Scholar
36. Goett, H. J. and Bullivant, W. K. Tests of NACA 0009, 0012.and Airfoils in the Full-Scale Tunnel. NACA Report 647, 1938.Google Scholar