WITH the development of the high‐altitude aero‐engine the creation of a reliable and simple means of measurement for the determination of the power output in flight becomes a primary necessity. Apart from the fact that the results obtained in flight afford an immediate and exact indication of the actual operational stresses and avoid the errors of mathematical conversions, such a method has the advantage of producing quickly and directly, with normal apparatus, results which otherwise could only be obtained on special test stands with considerable expenditure in time and money.
Gilbert, E. and Ulrich, W. (1940), "The D.V.L. Hub Dynamometer: A Description of the Design and Operation of an Instrument Utilizing the Film‐Scratching Method", Aircraft Engineering and Aerospace Technology, Vol. 12 No. 11, pp. 327-328. https://doi.org/10.1108/eb030712
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