Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift

Margolis, Kenneth

Editorial: BiblioGov
ISBN 10: 1287268455 / ISBN 13: 9781287268451
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Reseña del editor: On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms. For a given taper ratio and aspect ratio, an appreciable reduction in wing wave-drag coefficient with increased sweepback is noted for the entire range of Mach number considered. For a given sweep and taper ratio, higher aspect ratios reduce the wing wave-drag coefficient at substantially subcritical supersonic Mach numbers. At Mach numbers approaching the critical value, that is, a value equal to the secant of the sweepback angle, the plan forms of low aspect ratio have lower drag coefficients. Calculations for wings of equal root bending stress (and hence different aspect ratio) indicate that tapering the wing reduces the wing wave-drag coefficient at Mach numbers considerably less than the critical value and a decrease of the drag coefficient with taper at Mach numbers near the critical value.

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Título: Supersonic Wave Drag of Sweptback Tapered ...
Editorial: BiblioGov
Encuadernación: PAPERBACK
Condición del libro: New

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Kenneth Margolis
Publicado por Bibliogov, United States (2013)
ISBN 10: 1287268455 ISBN 13: 9781287268451
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Descripción Bibliogov, United States, 2013. Paperback. Condición: New. Language: English . Brand New Book ***** Print on Demand *****.On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms. For a given taper ratio and aspect ratio, an appreciable reduction in wing wave-drag coefficient with increased sweepback is noted for the entire range of Mach number considered. For a given sweep and taper ratio, higher aspect ratios reduce the wing wave-drag coefficient at substantially subcritical supersonic Mach numbers. At Mach numbers approaching the critical value, that is, a value equal to the secant of the sweepback angle, the plan forms of low aspect ratio have lower drag coefficients. Calculations for wings of equal root bending stress (and hence different aspect ratio) indicate that tapering the wing reduces the wing wave-drag coefficient at Mach numbers considerably less than the critical value and a decrease of the drag coefficient with taper at Mach numbers near the critical value. Nº de ref. del artículo: APC9781287268451

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Margolis, Kenneth
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ISBN 10: 1287268455 ISBN 13: 9781287268451
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Descripción BiblioGov, 2016. Paperback. Condición: New. PRINT ON DEMAND Book; New; Publication Year 2016; Not Signed; Fast Shipping from the UK. No. book. Nº de ref. del artículo: ria9781287268451_lsuk

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Kenneth Margolis
Publicado por Bibliogov, United States (2013)
ISBN 10: 1287268455 ISBN 13: 9781287268451
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Descripción Bibliogov, United States, 2013. Paperback. Condición: New. Language: English . Brand New Book ***** Print on Demand *****. On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms. For a given taper ratio and aspect ratio, an appreciable reduction in wing wave-drag coefficient with increased sweepback is noted for the entire range of Mach number considered. For a given sweep and taper ratio, higher aspect ratios reduce the wing wave-drag coefficient at substantially subcritical supersonic Mach numbers. At Mach numbers approaching the critical value, that is, a value equal to the secant of the sweepback angle, the plan forms of low aspect ratio have lower drag coefficients. Calculations for wings of equal root bending stress (and hence different aspect ratio) indicate that tapering the wing reduces the wing wave-drag coefficient at Mach numbers considerably less than the critical value and a decrease of the drag coefficient with taper at Mach numbers near the critical value. Nº de ref. del artículo: APC9781287268451

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Kenneth Margolis
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ISBN 10: 1287268455 ISBN 13: 9781287268451
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Descripción BiblioGov. Paperback. Condición: New. This item is printed on demand. 52 pages. Dimensions: 9.7in. x 7.4in. x 0.1in.On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms. For a given taper ratio and aspect ratio, an appreciable reduction in wing wave-drag coefficient with increased sweepback is noted for the entire range of Mach number considered. For a given sweep and taper ratio, higher aspect ratios reduce the wing wave-drag coefficient at substantially subcritical supersonic Mach numbers. At Mach numbers approaching the critical value, that is, a value equal to the secant of the sweepback angle, the plan forms of low aspect ratio have lower drag coefficients. Calculations for wings of equal root bending stress (and hence different aspect ratio) indicate that tapering the wing reduces the wing wave-drag coefficient at Mach numbers considerably less than the critical value and a decrease of the drag coefficient with taper at Mach numbers near the critical value. This item ships from La Vergne,TN. Paperback. Nº de ref. del artículo: 9781287268451

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Kenneth Margolis
Publicado por BiblioGov (2013)
ISBN 10: 1287268455 ISBN 13: 9781287268451
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Descripción BiblioGov, 2013. Condición: New. book. Nº de ref. del artículo: M1287268455

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