Transonic aerodynamics - History and statement of the problem

An historical account is given of the state of transonic aerodynamics research and theorization before 1940, and at selected points between that year and 1975, in order to provide a basis for the understanding and evaluation of the most recent developments in the field. Intensive development began during the Second World War, when fighter aircraft diving at speeds in excess of Mach 0.8 underwent buffeting and longitudinal trim shift effects. By 1960, transonic small disturbance theory had been established as a mathematical model for the prediction of the aerodynamic properties of airfoils, wings, and bodies throughout the Mach number range from zero to 1.5. In the years leading up to 1975, which saw the formulation of the transonic equivalence rule, improvements in the computational speed and memory capacity of computers became the most significant factor in the development of theory.

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[2]  J. W. Boerstoel Review of the Application of Hodograph Theory to Transonic Aerofoil Design and Theoretical and Experimental Analysis of Shock-free Aerofoils , 1976 .

[3]  W. Vincenti,et al.  Transonic flow past a wedge profile with detached bow wave , 1951 .

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[57]  D. Milton Second-order subsonic airfoil theory including edge effects , 1956 .

[58]  A. Bryson An experimental investigation of transonic flow past two-dimensional wedge and circular-arc sections using a Mach-Zehnder interferometer , 1951 .

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[60]  G. Y. Nieuwland,et al.  Transonic Airfoils: Recent Developments in Theory, Experiment, and Design , 1973 .

[61]  J. B. Mcdevitt,et al.  A correlation by means of transonic similarity rules of experimentally determined characteristics of a series of symmetrical and cambered wings of rectangular plan form , 1955 .

[62]  Howard W Emmons Flow of a compressible fluid past a symmetrical airfoil in a wind tunnel and in free air , 1948 .

[63]  John R. Spreiter,et al.  Thin airfoil theory based on approximate solution of the transonic flow equation , 1957 .

[64]  John Stack The NACA High-Speed Wind Tunnel and Tests of Six Propeller Sections , 1934 .

[65]  Robert T. Jones,et al.  Properties of low-aspect-ratio pointed wings at speeds below and above the speed of sound , 1946 .

[66]  E. M. Murman,et al.  Computation of Transonic Flows past Lifting Airfogs and Slender Bodies , 1972 .

[67]  Carl Kaplan The flow of a compressible fluid past a curved surface , 1943 .

[68]  Richard T. Whitcomb,et al.  A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound , 1952 .

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[70]  H. H. Pearcey,et al.  THE AERODYNAMIC DESIGN OF SECTION SHAPES FOR SWEPT WINGS , 1962 .

[71]  R. T. Whitcomb,et al.  Review of NASA supercritical airfoils , 1974 .

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[73]  John R. Spreiter,et al.  Slender-Body Theory Based On Approximate Solution of the Transonic Flow Equation , 1959 .

[74]  J. Spreiter Aerodynamics of Wings and Bodies at Transonic Speeds , 1959 .

[75]  John R Spreiter,et al.  On the range of applicability of the transonic area rule , 1956 .

[76]  A. Jameson Iterative solution of transonic flows over airfoils and wings, including flows at mach 1 , 1974 .

[77]  W. Sears,et al.  D. Supersonic and Transonic Small Perturbation Theory , 1954 .

[78]  Albert E. von Doenhoff,et al.  Tests of 16 related airfoils at high speed , 1934 .

[79]  W. Ogana,et al.  Derivation of an integral equation for transonic flows , 1977 .

[80]  W. Page Experimental Study of the Equivalence of Transonic Flow About Slender Cone-cylinders of Circular and Elliptic Cross Section , 1958 .

[81]  J. Zierep Die Integralgleichungsmethode zur Berechnung schallnaher Strömungen , 1964 .

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[83]  F. R. Bailey On the ‘computation of two- and three-dimensional steady transonic flows by relaxation methods , 1975 .