Joint report on an RCAF-DRB-NAE visit to N.A.C.A. Langley Laboratories to discuss aerodynamic problems of Avro CF-105 Aircraft: 19 November 1954

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Joint report on an RCAF-DRB-NAE visit to N.A.C.A. Langley Laboratories to discuss aerodynamic problems of Avro CF-105 Aircraft: 19 November 1954

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3406

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Report - Technical

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N.A.C.A. comments on CF-105 design problems are summarized as follows: (a) The Company’s estimate of zero lift drag at subsonic and supersonic speeds should be increased by 50 percent or more. (b) Substantial reductions in drag throughout the supersonic speed range should be possible by proper application of the area rule. (c) Present intake lip design is likely to result in prohibitive drag penalties at supersonic speeds. (d) The high drag due to lift associated with low aspect ratio delta wings makes them poor planforms for high endurance and long range. (e) The high drag due to lift is not improved by the negative camber proposed by the firm. Correctly designed positive camber should be used to reduce substantially both drag due to lift and trim drag. (f) A wind tunnel programme would be required to develop the means proposed by A.V. Roe to ensure intake stability. (g) The CF-105 wing planform is of the type which gives serious pitch-up tendencies. Cures developed in wind tunnels do not always work out in flight. (h) The directional stability characteristics of the CF-105 are poorer than had been experienced in the United States. A wind tunnel programme should be pursued. (i) All steps should be taken to ensure aerodynamic stability before resorting to electronic means. (j) It is possible that the use of elevons rather than separate elevators and ailerons would result in lower trim drag and higher reversal speed.

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Date / Time Period: 1954-Nov Pages: 10 Author: S/L W. Armstrong, A. Gilchrist, P. J. Pocock, R. J. Templin