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The induced drag factor of highly swept Delta wing at subsonic speeds

From National Research Council Canada

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Affiliation
  1. National Research Council Canada
FormatText, Technical Report
Physical description22 p.
SubjectAvro Arrow; Avro Canada; A.V. Roe Canada; Avro Canada CF-105 Arrow; CF-105; Canada supersonic jet; delta-winged supersonic interceptor
Abstract
The induced drag factor for delta wings with approximately 60 degrees of leading edge sweepback is found to be affected greatly by the aerofoil section shape. For thin sections (e.g. 5 percent) or thick sections with sharp noses the induced drag factor varies between 0.40 and 0.50. For thick sections (e.g. 10 percent) values of 0.8 and 0.9 can be obtained. The above results apply for Reynolds' Numbers of 4 million or greater. On the basis of limited data it appears that the induced drag factor for thin sectioned wings does not change over the subsonic Mach Number range.
Publication date
PublisherNational Research Council Canada. National Aeronautical Establishment. Aerodynamics Laboratory
Series
  • Laboratory Report (National Research Council Canada. National Aeronautical Establishment. Aerodynamics Laboratory), no. LR-105 (28 July 1954).
Is identical to
  • Pocock, P. J., and J. R. Westell. ‘The Induced Drag Factor of Highly Swept Delta Wing at Subsonic Speeds’. National Research Council Canada. National Aeronautical Establishment, 1954. .
LanguageEnglish
Peer reviewedNo
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Record identifier15207125-32b1-4214-a2aa-f6d9d6361808
Record created2020-11-26
Record modified2025-12-05
Date modified: