Hostname: page-component-586b7cd67f-dlnhk Total loading time: 0 Render date: 2024-11-28T18:26:00.240Z Has data issue: false hasContentIssue false
  • English
  • Français

Estimation of the Effects of Distortion on the Longitudinal Stability of Swept Wing Aircraft at High Speeds (Sub-Critical Mach Numbers)

Published online by Cambridge University Press:  07 June 2016

B. S. Campion
B. S. Campion*
Affiliation:
College of Aeronautics, Cranfleld
Get access

Summary

The effects of distortion on the longitudinal stability of swept wing aircraft at high speeds (sub-critical Mach numbers) are considered on a quasi-static basis. The method is based on the theory of Gates and Lyon but involves some extension of this theory.

The treatment of wing distortion is considered in some detail and the effects of built-in twist and camber and wing weight are included, using the so-called superposition method. The application of the analysis of Lyon and Ripley for investigating fuselage, tail and control circuit distortion is suggested, but means of modifying and simplifying this procedure where desirable are put forward.

The analysis is illustrated by means of a simple example of a swept wing fighter aircraft for which wing, fuselage and tail distortion effects are considered, and the results are discussed with reference to the individual and combined distortion effects, as well as the effect of compressibility.

Type
Research Article
Information
Aeronautical Quarterly , Volume 5 , Issue 5 , November 1954 , pp. 280 - 322
Copyright
Copyright © Royal Aeronautical Society. 1954

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. Gates, S. B. and Lyon, H. M. (1944). A Continuation of Longitudinal Stability and Control Analysis. Part I. R. & M. 2027, February 1944.Google Scholar
2. Lyon, H. M. and Ripley, J. (1945). A General Survey of the Effects of Flexibility of the Fuselage, Tail Unit and Control Systems on Longitudinal Stability and Control. R. & M. 2415, July 1945.Google Scholar
3. Brown, R. B., Holtby, K. F. and Martin, H. C. A Superposition Method for Calculating the Aeroelastic Behaviour of Swept Wings. Journal of the Aeronautical Sciences, Vol. 18, August 1951, pp. 531-42.CrossRefGoogle Scholar
4. Duncan, W. J. (1952). The Principles of the Control and Stability of Aircraft. Cambridge University Press, 1952.Google Scholar
5. Radok, J. R. M. (1952). Dynamic Aeroelasticity of Aircraft with Swept Wings. College of Aeronautics Report No. 58, April 1952.Google Scholar
6. Owen, P. R. (1944). The Effect of Compressibility on Longitudinal Stability Below the Shock Stall. R.A.E. Report Eero. 1829, March 1944.Google Scholar
7. Küchemann, D. (1950). A Simple Method for Calculating the Span and Chordwise Loadings on Thin Swept Wings. R.A.E. Report Aero. 2392, August 1950.Google Scholar
8. Duncan, W. J. (1943). The Representation of Aircraft Wings, Tails and Fuselages by Semi-rigid Structures in Dynamic and Static Problems, R. & M. 1904, February 1943.Google Scholar
9. Multhopp, H. (1950). Methods for Calculating the Lift Distribution of Wings (Subsonic Lifting Surface Theory). R.A.E. Report Aero. 2353, January 1950.Google Scholar
10. Garner, H. C. (1949). Theoretical Calculations of the Distribution of Aerodynamic Loading on a Delta Wing. R. & M. 2819, May 1949.Google Scholar
11. Weissinger, J. (1947). The Lift Distribution of Swept-back Wings. N.A.C.A. T.M. 1120, March 1947.Google Scholar
12. De Young, J. (1947). Theoretical Additional Span Loading Characteristics of Wings with Arbitrary Sweep, Aspect Ratio and Taper Ratio. N.A.C.A. T.N. 1491. December 1947.Google Scholar
13. Diederich, F. W. (1947). A Simple Method for Obtaining the Spanwise Lift Distribution on Swept Wings. N.A.C.A. R.M. L7107, September 1947.Google Scholar
14. Stanton-Jones, R. (1950). An Empirical Method for Rapidly Estimating the Loading Distributions on Swept-back Wings. College of Aeronautics Report No. 32, January 1950.Google Scholar
15. Falkner, V. M. (1943). The Calculation of Aerodynamic Loading on Surfaces of Any Shape. A.R.C. R. & M. 1910, August 1943.Google Scholar
16. Collingbourne, J. R. (1952). The Estimation of Lift Curve Slope at Subsonic Mach Numbers. R.A.E. T.N. Aero. 2145, January 1952.Google Scholar
17. Goldstein, S. and Young, A. D. (1943). Linear Perturbation Theory of Compressible Flow with Application to Wind Tunnel Interference. R. & M. 1909, July 1943.Google Scholar
18. Neumark, S. (1948). Dynamic Longitudinal Stability in Level Flight including the Effects of Compressibility and Variations of Atmospheric Characteristics with Height. R.A.E. Report Aero. 2265, August 1948.Google Scholar
19. Hall, A. H. (1951). An Experimental Study of the Static Stiffness and Deformation of Swept Wings with Uniform Chord. Third Anglo-American Aeronautical Conference, Brighton, 1951. Royal Aeronautical Society.Google Scholar
20. Diederich, F. W. and Foss, K. A. (1951). Charts and Approximate Formulas for the Estimation of Aeroelastic Effects on the Loading of Swept and Unswept Wings. N.A.C.A. T.N. 2608, September 1951.Google Scholar
21. Martin, H. C. and Gursahaney, H. J. (1951). Deflection of Swept Cantilever Surfaces. Journal of the Aeronautical Sciences, Vol. 18, December 1951.CrossRefGoogle Scholar
22. McDonnell Aircraft Corporation (1949). Stress Analysis and Stress Measurements for Swept Wings having Ribs Parallel to the Airstream. Report No. 1127, June 1949.Google Scholar
23. Hemp, W. S. (1950). On the Application of Oblique Co-ordinates to Problems of Plane Elasticity and Swept-back Wings. College of Aeronautics Report No. 31, January 1950.Google Scholar
24. Williams, M. L. (1952). A Review of Certain Analysis Methods for Swept Wing Structures. Journal of the Aeronautical Sciences, Vol. 19, September 1952, pp. 615–629.CrossRefGoogle Scholar
25. Pinsker, W. J. G. (1950). A Note on the Dynamic Stability of Aircraft at High Subsonic Speeds when Considering Unsteady Flow. R.A.E. Report Aero. 2378, May 1950.Google Scholar