Hostname: page-component-cd9895bd7-7cvxr Total loading time: 0 Render date: 2024-12-28T05:41:03.518Z Has data issue: false hasContentIssue false
  • English
  • Français

Estimation of Maximum Lift of Swept Wings at Low Mach Number.

Published online by Cambridge University Press:  04 July 2016

C. L. Bore  and
A. T. Boyd
C. L. Bore
Affiliation:
Hawker Aircraft Ltd
A. T. Boyd
Affiliation:
Hawker Aircraft Ltd
Get access Rights & Permissions [Opens in a new window]

Summary:

A semi-empirical method is given, together with systematic data sufficient for estimating the maximum lift characteristics of wings at Mach numbers below 0·6. The method gives the effect of sweep, aspect ratio, taper ratio, camber, leading-edge radius, maximum-thickness position and Reynolds number. The accuracy is good for most wings at full-scale Reynolds numbers, but deteriorates for wings with trailing-edge angles greater than about 12° (which for conventional sections correspond with thickness/chord ratios about 0·140), and for heavily cambered sections.

Type
Research Article
Information
The Aeronautical Journal , Volume 67 , Issue 628 , April 1963 , pp. 227 - 239
Copyright
Copyright © Royal Aeronautical Society 1963

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.Maki, R. L. The Use of Two-Dimensional Section Data to Estimate the Low Speed Wing Lift Coefficient at which Section Stall First Appears on a Swept Wing. NACA RM.A51.E.15 (TIB/2827), July 1951.Google Scholar
2. Sweptback Wings: Range of Lift Coefficients for Which Separation Effects are Negligible. Aerodynamics Technical Note AE.53, English Electric Co. Ltd., July 1951.Google Scholar
3.Abbott, and Von Doenhoff, . The Theory of Wing Sections. McGraw-Hill Book Co., Inc., 1949.Google Scholar
4.Tinling, B. E. and Kolk, W. R. The Effects of Mach Num ber and Reynolds’ Number on the Aerodynamic Charac teristics of Several 12 Per Cent Wings Having 35° of Sweepback and Various Amounts of Camber. NACA RM.A50 K27, 1951.Google Scholar
5.Franks, . Tests in the Ames 40- by 80-foot Wind Tunnel of Two Airplane Models Having Aspect Ratio 2 Trapezoidal Wings at Taper Ratios 033 and 0-20. NACA RM.A52.L.16 (TIB.3611), February 1953.Google Scholar
6.Comisarow, Schuldenfrei and Goodson, . Stability and Control Characteristics of a Complete Airplane Model Having a Wing with Quarter-Chord Line Swept Back 40°, Aspect Ratio 2·50, and Taper Ratio 0·42. NACA TN 2482, December 1951.Google Scholar
7.Allen, . Experimental Investigation of the Effects of Planform Taper on the Aerodynamic Characteristics of Symmetrical Unswept Wings of Varying Aspect Ratio. NACA RM.A53C 19 (TIB 3742), May 1953.Google Scholar
8.Becht, R. E. and Byrnes, A. L. Investigation of the Low- Speed Aerodynamic Characteristics of a Variable Sweep Air plane Model with a Wing Having Partial-Span Cambered- Leading-Edge Modifications. NACA RM.L52 G08a (TIB.4371), September 1952.Google Scholar
9.Purser, and Spearman, . Wind-Tunnel Tests at Low Speed of Swept and Yawed Wings Having Various Planforms. NACA RM.L7 D23 (TIB 1352), May 1947.Google Scholar
10.Trouncer, and Moss, . Low Speed Wind Tunnel Tests on Two 45° Sweptback Wings of Aspect Ratios 4·5 and 3·0 (Models A and B). RAE. TN. Aero 2210, June 1947.Google Scholar
11.Barn, P. S. Aerodynamic Characteristics of a 40° Swept Back Wing at Aspect Ratio 4·5. CoA Note No. 65, May 1957.Google Scholar
12.Hills, and Moss, . Low Speed Tunnel Tests on the Boulton and Paul Delta (E/27/46). R.A.E. T.N. Aero 2024, October 1949.Google Scholar
13.Bore, C. L. and Boyd, A. T. The Influence of Planform and Section on Maximum Lift at Mach Numbers up to 0·6. Hawker Project Office Report P.O.R. 129, November 1961.Google Scholar
14.Mccormack, G. M. and Cook, W. L. A Study of Stall Phenomena on a 45° Swept Forward Wing. NACA T.N. 1797, January 1949.Google Scholar
15.Mccormack, G. M. and Stevens, V. I. An Investigation of the Low-Speed Stability and Control Characteristics of Swept-Forward and Swept-Back Wings in the Ames 40- by 80-foot Wind Tunnel. NACA RM.A6 K15 (TIL 1362), June 1947.Google Scholar
16.Boltz, and Kolbe, . The Forces and Pressure Distribution at Subsonic Speeds on a Cambered and Twisted Wing Having 45° of Sweepback, an Aspect Ratio of 3, and a Taper Ratio of 0·5. NACA RM.A52 D22 (TIB 3268), July 1952.Google Scholar
17.Kirby, and Holford, . LOW Speed Tunnel Tests on a l/5th Scale Model of a Single-Jet Fighter with a 40° Sweptback Wing (Hawker F.3/48). R.A.E. T.N. Aero 2382, June 1950.Google Scholar
18.Anderson, R. F. Determination of the Characteristics of Tapered Wings. NACA Report 572, 1936.Google Scholar
19.Anderson, R. F. The Experimental and Calculated Charac teristics of 22 Tapered Wings. NACA Report 627, 1938.Google Scholar
20.Salter, C, Miles, J. W. and Lee, H. M. Tests on a Swept- Back Wing and Body in the Compressed Air Tunnel. A.R.C. Perf. 671, May 1950.Google Scholar
21.Ross, J. G., Hills, R. and Lock, R. C. Wind Tunnel Tests on a 90° Apex Delta Wing of Variable Aspect Ratio (Part 1: General Stability). R.A.E. Report Aero 2333 (C.P. 83), August 1949.Google Scholar
22.Spence, , A. Model Tests of Fowler Flaps, Slats and Nose Flaps on an Aircraft With 40° Swept Back Wing. R.A.E. Report Aero 2302 (R & M 2752), November 1948.Google Scholar
23.Griner, R. F. and Foster, G. V. Low-Speed Longitudinal and Wake Air-Flow Characteristics at a Reynolds’ Number of 6X106 of a 52° Sweptback Wing Equipped with Various Spans of Leading-Edge and Trailing Edge Flaps, a Fuselage and a Horizontal Tail at Various Vertical Positions. NACA RM L.50 K.29 (TIL.2633), February 1951.Google Scholar
24.Palme, H. O. Summary of Stalling Characteristics and Maximum Lift of Wings at Low Speeds. SAAB TN 15, April 1953.Google Scholar
25.Palme, H. O. Summary of Wind Tunnel Data for High- Lift Devices on Swept Wings. SAAB TN 16, April 1953.Google Scholar
26.Palme, H. O. Maximum Lift for Landing of Swept Wing Airplanes. SAAB TN 17, April 1953.Google Scholar
27. Hunter Prototypes: Lift and Buffet Boundaries. Hawker F.D.R. 52, October 1953.Google Scholar
28.Jordan, T. S. R. Unpublished Note. Hawker Aircraft Ltd., January 1961.Google Scholar