Restricted accessMoreSectionsView PDF ToolsAdd to favoritesDownload CitationsTrack Citations ShareShare onFacebookTwitterLinked InRedditEmail Cite this article Nonweiler Terence R. F. 1999Heat shield design for re-entry and launch. The use of conduction-assisted radiation on sharp-edged wingsPhil. Trans. R. Soc. A.3572197–2225http://doi.org/10.1098/rsta.1999.0428SectionRestricted accessHeat shield design for re-entry and launch. The use of conduction-assisted radiation on sharp-edged wings Terence R. F. Nonweiler Terence R. F. Nonweiler Victoria University, Wellington, New Zealand and APECS Ltd, 3 Hawkley Hurst, Hawkley, Hants GU33 6NS, UK Google Scholar Find this author on PubMed Search for more papers by this author Terence R. F. Nonweiler Terence R. F. Nonweiler Victoria University, Wellington, New Zealand and APECS Ltd, 3 Hawkley Hurst, Hawkley, Hants GU33 6NS, UK Google Scholar Find this author on PubMed Search for more papers by this author Published:01 August 1999https://doi.org/10.1098/rsta.1999.0428AbstractThe 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 be 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 lb ft−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 exceed more than 2 kPa (40 lbf ft−2). We cite values of less than this that relate to the design of a reentry vehicle with a wing loading of only 680 Pa (14 and a ¼ lbf ft7minus;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 higher loading and to regions of lower sweep, including at or near the wing apex where the heating rates are most intense. Previous ArticleNext Article VIEW FULL TEXT DOWNLOAD PDF FiguresRelatedReferencesDetailsCited by Larrimbe L, Pettinà M, Nikbin K, Jones E, Katz A, Hawkins C, DeCerbo J, Brown P, Vandeperre L and White M (2016) High Heat Flux Laser Testing of HfB 2 Cylinders , Journal of the American Ceramic Society, 10.1111/jace.14474, 100:1, (293-303), Online publication date: 1-Jan-2017. Kumar S and Mahulikar S (2015) Selection of Materials and Design of Multilayer Lightweight Passive Thermal Protection System, Journal of Thermal Science and Engineering Applications, 10.1115/1.4031737, 8:2, Online publication date: 1-Jun-2016. East R (2010) Re-Entry Vehicle Flight Profiles Encyclopedia of Aerospace Engineering, 10.1002/9780470686652.eae318 Squire T and Marschall J (2010) Material property requirements for analysis and design of UHTC components in hypersonic applications, Journal of the European Ceramic Society, 10.1016/j.jeurceramsoc.2010.01.026, 30:11, (2239-2251), Online publication date: 1-Aug-2010. Savino R, De Stefano Fumo M, Paterna D and Serpico M (2005) Aerothermodynamic study of UHTC-based thermal protection systems, Aerospace Science and Technology, 10.1016/j.ast.2004.12.003, 9:2, (151-160), Online publication date: 1-Mar-2005. Townend L (2001) Domain of the Scramjet, Journal of Propulsion and Power, 10.2514/2.5865, 17:6, (1205-1213), Online publication date: 1-Nov-2001. This Issue01 August 1999Volume 357Issue 1759Theme Issue ‘Hypersonic aircraft: lifting re–entry and launch’ compiled by L. H. Townend Article InformationDOI:https://doi.org/10.1098/rsta.1999.0428Published by:Royal SocietyPrint ISSN:1364-503XOnline ISSN:1471-2962History: Published online01/08/1999Published in print01/08/1999 License: Citations and impact Keywordsleading edge designeffect of roundingconducting–plate theoryconduction–assisted coolingre–entry heatingsharp–edge temperature