Hostname: page-component-586b7cd67f-r5fsc Total loading time: 0 Render date: 2024-11-30T15:09:51.201Z Has data issue: false hasContentIssue false
  • English
  • Français

The Drag Due to Lift of Plane Wings at Subsonic Speeds*

Published online by Cambridge University Press:  04 July 2016

D. Gardner  and
J. Weir
D. Gardner
Affiliation:
British Aircraft Corporation, Warton
J. Weir
Affiliation:
British Aircraft Corporation, Warton
Get access Rights & Permissions [Opens in a new window]

Summary

This note outlines a method for the prediction of drag due to lift of plane wings at Mach numbers below drag divergence and Reynolds numbers above 106. The method is based on the correlation of a number of wind tunnel measurements in terms of the effect of viscosity on lift curve slope. A comparison is made of the accuracy of estimating the induced drag factor, k, using this method, with the method of ret. 1, and it is shown that considerable improvement has been made, and that, in general, the predicted value of k is within 10% of experiment.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 70 , Issue 665 , May 1966 , pp. 595 - 599
Copyright
Copyright © Royal Aeronautical Society 1966

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.)

Footnotes

*

This note is an abridged version of ref. 42 which was written in fulfilment of Ministry of Aviation Contrast No. KU/4/025/CB53a.

References

1. Rutherford, and Frost, . Subsonic Wing Span Efficiency. AIAA Journal, April 1963.Google Scholar
2. Polhaumus, E. C. A Note on the Drag Due to Lift of Rectangular Wings of Low Aspect Ratio. NACA TN 3325, 1955.Google Scholar
3. Polhaumus, E. C. Drag Due to Lift at Mach Numbers up to 20. NACA TIL 5900/RML 53 I22b, 1953.Google Scholar
4. Garner, . Method for the Rapid Estimation of Theoretical Spanwise Loading due to a Change of Incidence. RAeS Transonic Data Memorandum 6403 and 6208, 1964.Google Scholar
5. Lift Curve Slope of Swept and Tapered Wings. RAeS Data Sheets on Wings, 01.01.01.Google Scholar
6. Slope of Lift Curve for Two-Dimensional Flow. RAeS Data Sheets on Wings, 01.01.05.Google Scholar
7. Collingbourne, J. R. The Estimation of Lift Curve Slope at Subsonic Mach Numbers. RAE Aero TN 2145.Google Scholar
8. Diederich, F. W. A Planform Parameter for Correlating Certain Aerodynamic Characteristics of Swept Wings. NACA TN 2335, 1951.Google Scholar
9. Bagley, J. A. Aerodynamic Principles for the Design of Swept Wings. Progress in Aeronautical Sciences, Vol 3. Pergamon Press, 1962.CrossRefGoogle Scholar
10. Abbott, I. H. and Von Doenoff, A. E. Theory of Wing Sections. Dover Publications, 1949.Google Scholar
11. Loftin, L. K. Jr. and Bursnall, W. J. The Effects of Variations in Reynolds Number between 3X106 and 25X106 upon the Aerodynamic Characteristics of a Num ber of NACA 6-Series Aerofoil Sections. NACA R 964, 1950.Google Scholar
12. Jones, R., Miles, J. W. and Pusey, P. S. Experiments in the Compressed Air Tunnel on Swept Back Wings Including Two Delta Wings. ARC R & M 2871, 1954.Google Scholar
13. Tinting, B. E. and Kolk, W. R. The Effects of Mach Number and Reynolds Number on the Aerodynamic Characteristics of Several 12 Per Cent Thick Wings having 35° of Sweepback and Various Amounts of Camber. NACA TIB 2629/RMA50K27, 1951.Google Scholar
14. Allen, E. C. Experimental Investigation of the Effects of Planform on the Aerodynamic Characteristics of Symmetrical Unswept Wings of Varying Aspect Ratio. NACA TIB 3742/RMA53C19, 1953.Google Scholar
15. Palmer, W. E. Effect of Reduction in Thickness from 6 to 2 percent and Removal of the Pointed Tips on the Subsonic Static Longitudinal Stability Characteristics of a 60° Triangular Wing in Combination with a Fuselage. NACA TIB 3862/RML53F24, 1953.Google Scholar
16. Kolbe, C. D. and Bandettine, A. Investigation in the Ames 12-Foot Pressure Wind Tunnel of a Model Horizontal Tail of Aspect Ratio 3 and Taper Ratio 05 Having the Quarter Chord Line Swept Back 45°. NACA TIB 2780/RMA51D02, 1951.Google Scholar
17. Graham, D. and Evans, W. T. Investigation of the Effects of an Airfoil Section Modification on the Aerodynamic Characteristics at Subsonic and Supersonic Speeds of a Thin Swept Wing of Aspect Ratio 3 in Combination with a Body. NACA TIB 4721/RMA55D11, 1955.Google Scholar
18. Reynolds, R. M. and Smith, D. W. Aerodynamic Study of a Wing Fuselage Combination Employing a Wing Swept Back 63°—Subsonic Mach and Reynolds Number Effects on the Characteristics of the Wing and on the Effectiveness of an Elevon. NACA TIB 1942/RMA8D20, 1948.Google Scholar
19. Wetzel, B. E. Effect of Taper Ratio on Lift, Drag, and Pitching Moment Characteristics of Thin Wings of Aspect Ratio 3 with 531° Sweepback of Leading Edge at Subsonic and Supersonic Speeds. NACA TIB 4535/RMA54J20, 1955.Google Scholar
20. Johnson, B. H. Jr. and Shibata, H. H. Characteristics Throughout the Subsonic Speed Range of a Plane Wing and of a Cambered and Twisted Wing, both having 45° of Sweepback. NACA TIB 2812/RMA 51D27, 1951.Google Scholar
21. 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 TIB 2894/RMA51G31, 1951.Google Scholar
22. Hall, C. F. Lift, Drag and Pitching Moment of Low-Aspect Ratio Wings at Subsonic and Supersonic Speeds. NACA TIL 3646/RMA53A30, 1953.Google Scholar
23. Kuhn, R. E. and Wiggins, J. W. Wind Tunnel Investigation of the Aerodynamic Characteristics in Pitch of Wing-fuselage Combinations at High Subsonic Speeds. NACA TIL 3080/RML52A29, 1952.Google Scholar
24. Smith, D. W. and Heitmeyer, J. C. Lift, Drag and Pitching Moment of Low Aspect Ratio Wings at Subsonic and Supersonic Speeds—Plane Triangular Wing of Aspect Ratio 2 with NACA 0008—63 Section. NACA TIL 2606/RMA50K20,1950.Google Scholar
25. Lipson, S. and Barnett, U. R. Jr. Force and Pressure Investigation at Large Scale of a 49° Sweptback Semispan Wing Having NACA 65A006 Sections and Equipped with Various Slat Arrangements. NACA TIB 3001/RML51K26, 1952.Google Scholar
26. Emerson, H. F. Wind Tunnel Investigations of the Effect of Clipping the Tips of Triangular Wings of Different Thickness, Camber and Aspect Ratio—Transonic Bump Method. NACATN3671.Google Scholar
27. Graham, D. Chordwise and Spanwise Loadings Measured at Low Speeds on a Large Triangular Wing Having an Aspect Ratio of 2 and a Thin Subsonic Airfoil Section. NACA TIB 2331/RMA50A04a, 1950.Google Scholar
28. Scallion, W. I. Low Speed Investigation of the Effects of Nacelles on the Longitudinal Aerodynamic Characteristics of a 60° Sweptback Delta Wing-Fuselage Combination with NACA 65 A003 Airfoil Sections. NACA TIB 3252/RML 52 F04, 1952.Google Scholar
29. Heitmeyer, J. C. and Smith, W. G. Lift, Drag and Pitching Moment of Low Aspect Ratio Wings at Subsonic and Supersonic Speeds—Plane Triangular Wing or Aspect Ratio 2 with NACA 0003—63 Section. NACA TIB 2609/RMA50K24a, 1951.Google Scholar
30. Heitmeyer, J. C. Lift, Drag and Pitching Moment of Low Aspect Ratio Wings at Subsonic and Supersonic Speeds—Plane Triangular Wing of Aspect Ratio 3 with NACA 0003—63 Section. NACA TIB 2869/RMA51H02, 1951.Google Scholar
31. Osbourne, R. S. and Kelly, T. C. A Note on the Drag due to Lift of Delta Wings at Mach Numbers up to 20. NASA TN D-545, 1960.Google Scholar
32. Kuchemann, D., Weber, J. and Brebner, G. G. LOW Speed Tests on Wings of 45° Sweep. Part II. Balance and Pressure Measurements on Wings of Different Aspect Ratios. RAE Aero Rep 2419, 1951.Google Scholar
33. Loftin, L. K. Jr. and Smith, H. A. Aerodynamic Characteristics of 15 NACA Airfoil Sections at Seven Reynolds Numbers from 07X106 to 90X106. NACA TN 1945.Google Scholar
34. Adams, G. J. and Boyd, J. W. An Experimental Investigation of a Triangular Wing of Aspect Ratio 2 and a Body Warped to be Trimmed at M=2.24. NASA TIL 6388, 1959.Google Scholar
35. Wetzel, B. E. and Pfyl, F. A. Effects of Leading Edge Chord Extensions and an all-movable Horizontal Tail on the Aerodynamic Characteristics of a Wing-Body Combination Employing a Triangular Wing of Aspect Ratio 3 Mounted in a High Position at Subsonic and Supersonic Speeds. NACA TIB 4053/RMA53J14a, 1954.Google Scholar
36. Hightower, R. C. Lift, Drag and Pitching Moment of Low Aspect Ratio Wings at Subsonic and Supersonic Speeds—Comparison of Three Wings of Aspect Ratio 2 of Rectangular, Swept Back, and Triangular Planform, including effects of Thickness Distribution. NACA TIB 3609/RMA52L02, 1952.Google Scholar
37. Boyd, J. W., Migotsky, E. and Wetzel, B. E. A Study of Conical Camber for Triangular and Sweptback Wings. NACA TIL 4877/RMA55G19, 1955.Google Scholar
38. Huntley, E. Wind Tunnel Tests at Transonic and Supersonic Speeds to Investigate the Longitudinal Stability of a Model of the Avro 720 Aircraft. RAE TN Aero 2685, 1960.Google Scholar
39. McDonald, H. and Stoddart, J. A. P. On the Development of the Low Speed Turburlent Boundary Layer. BAC (Warton) Ltd. Aero TN Ae 225, 1965. To be published in the ARC R & M series.Google Scholar
40. Beasley, J. A. Estimates of the Lift Reduction due to Boundary Layer on Two-Dimensional Aerofoils. RAE Tech Rept No 64014, 1964.Google Scholar
41. Gardner, D. A Fortran II Programme to Evaluate Drag Due to Lift in Subsonic Flow. BAC (Warton) Ltd Fortran Prog No. 31.Google Scholar
42. Gardner, D. and Weir, J. The Drag due to Lift of Plane Wings at Subsonic Speeds. BAC (Warton) Report Ae227.Google Scholar