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Aerofoil Sections and Torsion

Aerofoil Sections and Torsion 44 AIRCRAFT ENGINEERIN G February, 1940 Geometrical Properties of Symmetrical N.A.C.A. Aerofoils for use in Torsional Calculations By F. David Th e chart accompanying this note refers to symmetrical aerofoils of the N.A.C.A. family, bu t the ordinary magnitude of th e mean camber will have no practical influence on th e results if it is also used for non-symmetrical aerofoils. Example To find the required area and perimeter of th e box between 11 per cent and 67 per cent behind the leading edge of N.A.C.A. Section Chord length = 90 ins., ... t = 0•12 x 90 = 10•8 ins. Area, from curve : A = 0•685 X 10•8 X 90 x 0•742 = 494 sq. in. Perimeter, from curve (for t/c = 0•l2) : Fro m the lower curve : A = 0•04, P = (2 + 0•04) X 90 = 183•6 ins. (P + y)67 per cent — (P + y)11 per cent = 0•543 X 183•6 = 99•6 ins. y = 0•805 X 10•8 = 8•7 ins. 11 percen t Perimeter of Box = 99•6 + 8•7 = 108•3 ins. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Aerofoil Sections and Torsion

David, F.
Aircraft Engineering and Aerospace Technology , Volume 12 (2): 1 – Feb 1, 1940
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030608
Publisher site
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Abstract

44 AIRCRAFT ENGINEERIN G February, 1940 Geometrical Properties of Symmetrical N.A.C.A. Aerofoils for use in Torsional Calculations By F. David Th e chart accompanying this note refers to symmetrical aerofoils of the N.A.C.A. family, bu t the ordinary magnitude of th e mean camber will have no practical influence on th e results if it is also used for non-symmetrical aerofoils. Example To find the required area and perimeter of th e box between 11 per cent and 67 per cent behind the leading edge of N.A.C.A. Section Chord length = 90 ins., ... t = 0•12 x 90 = 10•8 ins. Area, from curve : A = 0•685 X 10•8 X 90 x 0•742 = 494 sq. in. Perimeter, from curve (for t/c = 0•l2) : Fro m the lower curve : A = 0•04, P = (2 + 0•04) X 90 = 183•6 ins. (P + y)67 per cent — (P + y)11 per cent = 0•543 X 183•6 = 99•6 ins. y = 0•805 X 10•8 = 8•7 ins. 11 percen t Perimeter of Box = 99•6 + 8•7 = 108•3 ins.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Feb 1, 1940

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