Browsing Aeronautical Research Council Reports & Memoranda by Author "E. G. Broadbent"

Browsing Aeronautical Research Council Reports & Memoranda by Author "E. G. Broadbent"

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  • Determination of reversal speed of a wing with a partial-span flap and inset aileron 
    W. G. Molyneux; E. G. Broadbent (1950)
    Control reversal due to deformation of a wing with a partial-span flap and inset aileron is considered theoretically for the particular case of a flap held at the root end. The semi-rigid method is used. An investigation ...
  • The effect of structural damping on binary flutter 
    E. G. Broadbent; Margaret Williams (1956)
    The paper describes an investigation of the effect of structural damping in the torsion mode on wing flutter with the object of finding circumstances in which damping reduces the flutter speed. The drop in flutter speed ...
  • Elevator flutter involving two tabs 
    E. G. Broadbent; Mary Clarke (1954)
    An account is given of a theoretical flutter investigation in connection with an accident to a Sea Venom aircraft. The investigation covers both symmetric and antisymmetric flutter of the tailplane-elevator-tab system. The ...
  • Flutter of an all-moving tailplane 
    E. G. Broadbent; Margaret Williams (1957)
    Tailplane flutter is investigated theoretically for the following semi-rigid modes : (i) tailplane bending, frequency ω1; (ii) tailplane torsion, frequency ω2; (iii) tailplane rotation, frequency ω3; (iv) fuselage bending ...
  • Flutter problems of high-speed aircraft 
    E. G. Broadbent (1949)
    The flutter problems of high-speed aircraft are considered generally and specific consideration is then given to the new problems introduced by the use of new wing plan forms. The theoretical and experimental results on ...
  • A note on flutter of asymmetric controls 
    E. G. Broadbent; E. V. Hartley (1960)
    This Paper attempts to give some guidance on the question, of how best to approximate to an aircraft with an asymmetric elevator control for the purpose of flutter calculations. Two examples of asymmetric controls that ...
  • The rolling power of an elastic swept wing 
    E. G. Broadbent (1950)
    An iterative method of solution is given for the problem of loss in rolling power due to wing deformation. The method is applicable at subsonic or supersonic speeds, and compressibility effects are allowed for, provided ...
  • Some possible effects of transonic speeds on wing-aileron flutter 
    E. G. Broadbent; E. Violet Hartley (1959)
    A typical wing-aileron combination is taken and ternary flutter calculations between wing bending, wing torsion and aileron rotation are described. The results are plotted as graphs of flutter speed against aileron frequency ...
  • Some unseparated base flows with heat addition 
    E. G. Broadbent (1973)
    Analytical solutions are derived for a class of axisymmetric base flows with heat addition. The assumed upstream conditions are non-uniform in velocity and temperature, which vary with r in spherical polar coordinates (r, ...
  • A study of dynamic aeroelastic effects on the stability control and gust response of a slender delta aircraft 
    E. G. Broadbent; J. K. Zbrozek; E. Huntley (1971)
    In this report four previously unpublished notes, concerned with aeroelastic effects on a particular slender delta aircraft configuration, are collected together. Some general flutter calculations show that decreasing ...
  • A theoretical exploration of the flow about an electric arc transverse to an airstream using potential flow methods 
    E. G. Broadbent (1965)
    The arc cross section is supposed to be a region in which heat is supplied to a continuous stream and in which a body force acts. Pressure variations are assumed small so that incompressible potential flow methods can be ...
  • Vectorial analysis of flight flutter test results 
    E. G. Broadbent; E. Violet Hartley (1958)
    A binary flexure-torsion analysis has been made to check theoretically a method for the prediction of flutter which depends on plotting vectorially the amplitudes of response relative to the exciting force and extracting ...

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