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Titolo:
Heat shield design for re-entry and launch. The use of conduction-assistedradiation on sharp-edged wings
Autore:
Nonweiler, TRF;
Indirizzi:
Victoria Univ Wellington, Wellington, New Zealand Victoria Univ Wellington Wellington New Zealand Wellington, New Zealand APECS Ltd, Hawkley GU33 6NS, Hants, England APECS Ltd Hawkley Hants England GU33 6NS Hawkley GU33 6NS, Hants, England
Titolo Testata:
PHILOSOPHICAL TRANSACTIONS OF THE ROYAL SOCIETY OF LONDON SERIES A-MATHEMATICAL PHYSICAL AND ENGINEERING SCIENCES
fascicolo: 1759, volume: 357, anno: 1999,
pagine: 2197 - 2225
SICI:
1364-503X(19990815)357:1759<2197:HSDFRA>2.0.ZU;2-B
Fonte:
ISI
Lingua:
ENG
Keywords:
re-entry heating; leading edge design; conduction-assisted cooling; conducting-plate theory; sharp-edge temperature; effect of rounding;
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Physical, Chemical & Earth Sciences
Citazioni:
4
Recensione:
Indirizzi per estratti:
Indirizzo: Nonweiler, TRF Victoria Univ Wellington, Wellington, New Zealand Victoria Univ Wellington Wellington New Zealand Zealand
Citazione:
T.R.F. Nonweiler, "Heat shield design for re-entry and launch. The use of conduction-assistedradiation on sharp-edged wings", PHI T ROY A, 357(1759), 1999, pp. 2197-2225

Abstract

The conduction of heat within the material of a wing leading edge can be treated both simply and (usually) accurately by 'conducting-plate theory'. The theory leads to a concise 'reference solution' for the variation of temperature over a solid wedge-shaped nose that is heated by a boundary layer. This indicates the best choice of material, and we look at ways a given mass of the material may best be installed to reduce the nose temperature, without sacrificing the benefits that, a sharp-nosed wing may have to offer. It is shown that although these materials may be dense, a heavy mass is not required to achieve acceptable temperatures at the edge in hypersonic flight. Something perhaps between 5 and 10 kg per metre of edge (or say 3-7 lbft(-1)) is usually enough. However, the nose temperature depends on sweepback and surface pressure. To avoid temperatures of 1600 K or more at a highly swept sharp edge in hypersonic flight, it is necessary that neither the wing loading nor the surface pressure exceeds more than 2 kPa (40 lbf ft(-2)). We cite values of less than this that relate to the design of a re-entry vehicle with a wing loading of only 680 Pa (141/4 lbf ft(-2)). However, rounding the nose (with a radius usually of just a few millimetres) can provide reductions of up to perhaps 20% in the nose temperature. This allows this form of temperature control to be extended to wings of higherloading and to regions of lower sweep, including at or near the wing apex where the heating rates are most intense.

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Documento generato il 04/12/20 alle ore 22:46:16