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Aeronautical Research in Sweden

Published online by Cambridge University Press:  28 July 2016

Bo K. O. Lundberg
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Extract

I wish first to express my deep appreciation for having been invited by the Council of the Royal Aeronautical Society to present a lecture on aeronautical research in Sweden. As the subject is a very broad one, it was necessary for me to consider rather thoroughly what would be expected from this paper and thus, which limitations in its scope should preferably be made.

Before the 1939-45 War it was possible to design new, successful aeroplanes mainly on the basis of experience from previous types in combination with generally available design information, such as aerofoil data. The success was, in fact, often more dependent on the skill of the designer than on the amount of research and detailed aerodynamic and structural testing done. After the advent of jet propulsion and transonic and supersonic speeds this situation changed radically. Nowadays a substantial amount of basic and applied research, as well as scientifically performed development work, is a necessity for any country, regardless of size, attempting to produce its own designs of efficient and safe aircraft.

Type
Research Article
Information
The Aeronautical Journal , Volume 59 , Issue 538 , October 1955 , pp. 647 - 681
Copyright
Copyright © Royal Aeronautical Society 1955

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References

1. Löfkvist, H.E. (1954). Aeronautical Research and Development in Sweden. Financial Background and Organisation. Aeronautical Engineering Review, December 1954, and SAAB Sonics, No. 22, 1955.Google Scholar
2.Landskrona Museiförenings Arsbok, 1944.Google Scholar
3.Sweden's New Fighter. Flight, 26th August 1943.Google Scholar
4. Jacobs, W. (1953). Theoretical and Experimental Investigations of Interference Effects of Delta Wing–Vertical Tail Combinations with Yaw. F.F.A. Report 49, 1953.Google Scholar
5. Petersohn, E. G. M. (1952). Some Experimental Investigations on the Influence of Wall Boundary Layers upon Wind Tunnel Measurements at High Subsonic Speeds. F.F.A. Report 44, 1952.Google Scholar
6. Berndt, S. B. (1952). Approximate Calculation of the Influence of Wall Boundary Layers upon the Blockage Interference in a High Speed Wind Tunnel. F.F.A. Report 45, 1952.Google Scholar
7. Berndt, S. B. (1954). On the Influence of Wall Boundary Layers in Closed Transonic Test Sections. F.F.A. T.N. AE-262:1, 1954 (Unpublished).Google Scholar
8. Petersohn, E. G. M. (1951). Investigations to Reduce the Wall Interference Effects in Wind Tunnel Tests at High Subsonic Velocities. I. Orienterande undersökning vid symmetrisk tvadimensionell stromning. F.F.A. T.N. AE-196:1, 1951 (Unpublished).Google Scholar
9. Drougge, G. (1949). A Method for the Continuous Variation of the Mach Number in a Supersonic Wind Tunnel and Some Experimental Results Obtained at Low Supersonic Speeds. F.F.A. Report 29, 1949.Google Scholar
10. Drougge, G. (1952). Some Measurements at Low Supersonic Speeds by a Method for Continuous Variation of the Mach Number. F.F.A. Report 42, 1952.Google Scholar
11. Seddon, J. and Haverty, L. (1953). Note on an Application of the Tilting Plate Method of Mach Number Variation for Wind Tunnel Tests at Low Supersonic Speeds. A.R.C. C.P. 168, March 1953.Google Scholar
12. Fox, J. L. (1951). Supersonic Tunnel Investigation by Means of Inclined–Plate Technique to Determine Performance of Several Nose Inlets over Mach Number Range of 1-72 to 218. N.A.C.A. R.M. E50K14, 14th February 1951.Google Scholar
13. Drougge, G. (1953). An Experimental Investigation of the Influence of Strong Adverse Pressure Gradients on Turbulent Boundary Layers at Supersonic Speeds. F.F.A. Report 46, 1953.Google Scholar
14. Öhman, L. (1954). An Experimental Method of Determining the Drag of a Shock Wave with Application to a Ducted Body. F.F.A. Report 51, 1954.Google Scholar
15. Liepmann, H. W. (1950). On the Relation between Wave Drag and Entropy Increase. Douglas Report No. SM-13726, 1950.Google Scholar
16. Drougge, G. and Larsson, P. O. (1955). Pressure Measurements and Flow Investigations on Delta Wings at Supersonic Speed. F.F.A. Report 57, 1955.Google Scholar
17. Orlik–Rückemann, K. and Olsson, C. O. (1955). A Method for the Determination of the Damping–in–Pitch of Semi–Span Models in High–Speed Wind Tunnels, and Some Results for a Triangular Wing, 1955 (To be published in the F.F.A. Report Series).Google Scholar
18. Orlik–Rückemann, K. and Olsson, C. O. (1955). A Method for the Determination of the Damping–in–Roll in High–Speed Wind Tunnels and Some Initial Results for a Wing–Body Combination, 1955 (To be published in the F.F.A. Report Series).Google Scholar
19. Landahl, M. T. (1954). The Flow around Oscillating Low Aspect Ratio Wings at Transonic Speeds. K.T.H. AERO T.N. 40, 1954.Google Scholar
20. Berndt, S. B. (1951). On the Theory of Slowly Oscillating Delta Wings at Supersonic Speeds. F.F.A. Report 43, 1951.Google Scholar
21. Lundberg, B. K. O. (1945). Jämfürande utredning betraffande reaktions—och propellerdrift for flygplan (Comparative investigation concerning jet and airscrew propulsion of aircraft). F.F.A. T.N. PE-2, 1945 (Unpublished).Google Scholar
22. Lundberg, B. K. O. (1945). Reaktions–eller propellerdrift för flyglan? (Jet or Airscrew Propulsion of Aircraft?), “ Morgondagens Teknik,” 1945. (This book was published by The Swedish Association of Engineers and Architects celebrating the 75th anniversary of the issue of the journal Teknisk Tidskrifi).Google Scholar
23. Lundberg, B. K. O. (1947). Useful Load Ratio with Jet and Airscrew Propulsion of Aircraft. Journal of the Royal Aeronautical Society.August 1947.Google Scholar
24. Lundberg, B. K. O. (1945). Investigation concerning Optimum Aspect Ratio for Jet–Propelled Fighters. F.F.A. T.N. HU-196, Parts I to IV, 1945 (Unpublished).Google Scholar
25. Lundberg, B. K. O. (1947). Den maximala upptryckskoefficientens betydelse för snabba reaktionsflygplans lastförmaga (The importance of the maximum lift coefficient for the load capacity of high–speed jet aeroplanes), F.F.A. T.N. HU-186, 1947 (Unpublished).Google Scholar
26. Landahl, M. T. and Stark, J. E. (1953). An Electrical Analogy for Solving the Oscillating–Surface Problem for Incompressible Nonviscid Flow. K.T.H. AERO T.N. 34, 1953.Google Scholar
27. Oswatitsch, K. and Berndt, S. B. (1950). Aerodynamic Similarity at Axisymmetric Transonic Flow around Slender Bodies. K.T.H. AERO T.N. 15, 1950.Google Scholar
28. Oswatitsch, K. (1950). Similarity Laws for Hypersonic Flow. K.T.H. AERO T.N. 16, 1950.Google Scholar
29. Gullstrand, T. R. (1952). A Theoretical Discussion of Some Properties of Transonic Flow over Two–Dimensional Symmetrical Aerofoils at Zero Lift with a Simple Method to Estimate the Flow Properties. K.T.H. AERO T.N.25, 1952.Google Scholar
30. Keune, F. (1953). On the Subsonic, Transonic and Supersonic Flow around Low Aspect Ratio Wings with Incidence and Thickness. K.T.H. AERO T.N. 28, 1953.Google Scholar
31. Merbt, H. and Landahl, M. (1953). Aerodynamic Forces on Oscillating Low Aspect Ratio Wings in Compressible Flow. K.T.H. AERO T.N. 30, 1953.Google Scholar
32. Keune, F. and Oswatitsch, K. An Integral Equation Theory for the Transonic Flow around Slender Bodies of Revolution. K.T.H. AERO T.N. 37. To be published in the K.T.H. AERO T.N. Series.Google Scholar
33. Oswatitsch, K. (1952). Die Theoretische Arbeiten iiber Schallnahe Stromung am Flugtechnischen Institut der Koniglichen Technischen Hochschule, Stockholm. Paper presented at the 8th International Congress on Theoretical and Applied Mechanics in Istanbul, 1952.Google Scholar
34. Örnberg, T. (1954). A Note on the Flow around Delta Wings. K.T.H. AERO T.N. 38, 1954.Google Scholar
35. Wänström, F. (1952). The New SAAB Jet Wind Tunnel. SAAB Sonics, No. 17, 1952.Google Scholar
36. Stenstrom, L. (1950). The SAAB Gradient Tank—an Aid to Aeroplane Design. SAAB Sonics, No. 12, 1950.Google Scholar
37. Lind, B. (1953). Test Facilities due to the Compressed Air Magazine and the Steam Power Plant at Flygmotor. Flygmotor Technical Note 1, Trollhättan, 1953.Google Scholar
38. Rosén, J. (1954). The Design and Calibration of a Variable Mach Number Nozzle. K.T.H. Division of Steam Engineering, Report K.T.H. Å 2/61, 1954.Google Scholar
39. Anderson, R. (1949). Some Preliminary Information on Buckling and Ultimate Strength of Unstiffened Compression Skin Obtained through Bending and Compression Tests on Rectangular Cross Section Aluminium Tubes. F.F.A. Report 27, 1949.Google Scholar
40. Eggwertz, S. (1950). Buckling Stresses of Box–Beams under Pure Bending. F.F.A. Report 33, 1950..Google Scholar
41. Stowell, E. Z. (1951). Compressive Strength of Flanges. N.A.C.A. Report 1029, 1951.Google Scholar
42. Norr, A. and Olhager, A. Strength and Stiffness of Shear Webs with and without Lightening Holes and with and without Vertical Stiffeners. F.F.A. Technical Notes HU-371, 396, 422, 446, 476, 440, 479 and 512 (Unpublished). A summary of the five first–mentioned Technical Notes has been published in SAAB T.N. 29, “ Experimental Investigation of Shear Strength and Shear Deformation of Unstiffened Beams of 24 S-T Alclad with and without Flanged Lightening Holes,” by G. Anevi, 1954.Google Scholar
43. Noton, B. R. (1953). Structural Aspects of Swept–Back Wings. Aircraft Engineering, November 1953.Google Scholar
44. Noton, B. R. (1953). Experimental Investigation of the Stress Distribution in a Plastic Model of a 35° Swept Back Wing with Multi–Web Construction. F.F.A. Report 47, 1953.Google Scholar
45. Eggwertz, S. and Noton, B. R. (1954). Stress and Deflection Measurements on a Multicell Cantilever Box Beam with 30° Sweep. F.F.A. Report 53, 1954.Google Scholar
46. Eggwertz, S. (1954). Calculation of Stresses in a Swept Multicell Cantilever Box Beam with Ribs Perpendicular to the Spars and Comparison with Test Results. F.F.A. Report 54, 1954.Google Scholar
47. Noton, B. R. Investigation on Aluminium Honeycomb Cores for Sandwich Construction. To be published in the F.F.A. Report Series. Google Scholar
48. Wallgren, G. (1949). Fatigue Tests with Stress Cycles of Varying Amplitude. F.F.A. Report 28, 1949.Google Scholar
49. Lundberg, B. K. O. and Wallgren, G. (1949). A Study of Some Factors Affecting the Fatigue Life of Aircraft Parts with Application to Structural Elements of 24S-T and 75S-T Aluminium Alloys. F.F.A. Report 30, 1949.Google Scholar
50. Wallgren, G. (1953). Direct Fatigue Tests with Tensile and Compressive Mean Stresses on 24S-T Aluminium Plain Specimens and Specimens Notched by a Drilled Hole. F.F.A. Report 48, 1953 Google Scholar
51. Weibull, W. (1955). New Methods for Computing Parameters of Complete or Truncated Distributions. F.F.A. Report 58, 1955.Google Scholar
52. Weibull, W. (1955). Static Strength and Fatigue Properties of Threaded Bolts. F.F.A. Report 59, 1955.Google Scholar
53. Lundberg, B. K. O. (1955). Fatigue Life of Airplane Structures. The 18th Wright Brothers’ Lecture. Journal of the Aeronautical Sciences, June 1955. Also published as F.F.A. Report 60, 1955.Google Scholar
54. Weibull, W. (1954). The Propagation of Fatigue Cracks in Light–Alloy Plates. SAAB T.N. 25, 1954.Google Scholar
55. Rand, T. (1948). Statik for flygplanskal (Statics of Stressed–Skin Aeroplane Structure). Thesis for Doctor's Degree at K.T.H., 1948.Google Scholar
56. Rand, T. (1951). An Approximate Method for the Calculation of the Stresses in Sweptback Wings. Journal of the Aeronautical Sciences, January 1951.Google Scholar
57. Weibull, W. (1955). Scatter in Fatigue Life of 24S-T Flat Specimens. SAAB T.N. 32, 1955.Google Scholar
58. Weibull, W. (1954). A New Method for the Statistical Treatment of Fatigue Data. SAAB T.N. 30, 1954.Google Scholar
59. Weibull, W. (1954). The Static Strength and the Fatigue Strength of Riveted, Spotwelded and Redux–Bonded Joints in 24S-T Aluminium Alloy Sheet. SAAB T.N. 31, 1954.Google Scholar
60. Langefors, B. (1950). Improvement in Electric Computer Networks for Some Elastic Structures. SAAB T.N. 1, 1950. (1951). Structural Analysis of Swept–Back Wings by Matrix–Transformation. SAAB T.N. 3, 1951. (1952). Approximate Solution of Simultaneous Equations by means of Transformation of Variables. Applications to Aeronautical Problems. SAAB T.N. 7, 1952. (1953). Ill–Conditioned Matrices. SAAB T.N.22, 1953. (1953). A Suggested Method for Calculating the Stresses in Wings with Non–rectangular Plates. SAAB T.N. 23, 1953. (1953). Exact Reduction and Solution by Parts of Equation for Elastic Structures. SAAB T.N. 24, 1953.Google Scholar
61. Gustafsson, G. (1947). Some Basic Characteristics of Wire Strain Gauges and Bridge Circuits for these Gauges. F.F.A. Report 22, 1947.Google Scholar
62. Gustafsson, G. (1954). How to Use G–H Gauges. Characteristics and Applications of Resistance Strain Gauges, pp. 79-91. National Bureau of Standards Circular 528, 1954.Google Scholar