Browsing CoA. Reports by Title

Browsing CoA. Reports by Title

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  • The unsteady aerodynamic forces on deforming, low aspect ratio wings and slender wing-body combinations oscillating harmonically in a compressible flow 
    Milne, R. D. (College of Aeronautics, Cranfield., 1955-07)
    A method is presented whereby the 'Slender Body Theory' can be applied to the determination of the unsteady aerodynamic forces acting on slender wings and wing-body combinations experiencing harmonic deformations in a ...
  • The use of a potential flow tank for testing axi-symmetric contraction shapes suitable for wind tunnels 
    Babister, A. W.; Marshall, W. S. D.; Lilley, G. M.; Sills, E. C.; Deards, S. R. (College of Aeronautics, Cranfield., 1951-04)
    The report gives details of tests in the potential flow tank on a series of axi-symmetric contraction shapes. The tests were in connection with the design of the 8ft x 6ft wind tunnel and a water tunnel. Continues...
  • Vibration characteristics of a cantilever plate with swept-back leading edge 
    Heiba, A. E. (College of Aeronautics, Cranfield., 1982-10)
    The paper presents an experimental study of natural frequencies and modes of vibration of uniform cantilever plates. Sixteen planforms are tested by combining aspect ratios of 0.8, 1.2, 1.6 and 2 with leading edge sweep-back ...
  • Vibrations of a swept box 
    Radok, J. R. M. (College of Aeronautics, Cranfield, 1951-04)
    The equation of motion of a uniform swept box with stringers and ribs are deduced. For the case of vibrations of a cantilever they are transformed into integrated equations, an approximate method of solution of which is indicated.
  • Viscous flux limiters 
    Toro, E. F. (1991)
    We present Numerical Viscosity Functions, or NVFs, for use with Riemann-problem based shock-capturing methods as applied to viscous flows. In particular, viscous flux limiters are derived. The analysis pertain to a linear ...
  • Wave reflection near a wall 
    Robinson, A. (College of Aeronautics, Cranfield., 1950-05)
    The field of flow due to a shock wave or explanation wave undergoes a considerable modification in the neighbourhood of a rigid wall. It has been suggested that the resulting propagation of the disturbance upstream is ...
  • Wing body interference at supersonic speeds 
    Kirkby, S.; Robinson, A. (College of Aeronautics, Cranfield, 1947-04)
    The increment in lift due to wing-body interference at supersonic speed is calculated approximately for an untapered wing without sweepback.

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