Browsing by Author "Babister, A. W."

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    Flutter and divergence of sweptback and sweptforward wings
    (College of Aeronautics, Cranfield., 1950-06) Babister, A. W.
    In this note, the equations of the flexural-torsional flutter of a swept wing are established, assuming the wing to be semi-rigid and fixed at the root. The general effect of sweepback, wing stiffness and position of the inertia axis are determined. The critical speeds for flutter and for wing divergence are determined (i) for incompressible flow (ii) for compressible flow, assuming a modified Glauert correction. The critical flutter speed is in general higher for a sweptback wing having the same wing stiffness as the upswept wing; foe a swept forward wing, divergence will occur before flutter.
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    Measurements of the pressure distribution on swept back wings with trailing edge split flaps: summary of wind tunnel work at the College of Aeronautics 1948 - 50
    (College of Aeronautics, Cranfield., 1951-03) Babister, A. W.
    This is an interim report giving measurement s that have so far been made of pressure distribution on two untapered wings swept back 45◦, aspect ratio 2 and 4, fitted with both full span and part span trailing edge split flaps. The Reynolds number in these tests was about 0.5x106.
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    The use of a potential flow tank for testing axi-symmetric contraction shapes suitable for wind tunnels
    (College of Aeronautics, Cranfield., 1951-04) Babister, A. W.; Marshall, W. S. D.; Lilley, G. M.; Sills, E. C.; Deards, S. R.
    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...