01122nam0 22002653i 450 SUN009959320141029102355.133978-88-498-1678-50.0020141029d2006 |0itac50 baitaIT|||| |||||Essere re e non essere reCarlo di Borbone a Napoli e le attese deluse, 1734-1738Giuseppe CaridiSoveria MannelliRubbettino2006XV, 282 p.23 cm.001SUN00613082001 Saggi180210 Soveria MannelliRubbettino.Soveria MannelliSUNL000176Caridi, GiuseppeSUNV078223145014RubbettinoSUNV000666650ITSOL20181109RICASUN0099593UFFICIO DI BIBLIOTECA DEL DIPARTIMENTO DI LETTERE E BENI CULTURALI07 CONS Ve 352 07 UBL63 UFFICIO DI BIBLIOTECA DEL DIPARTIMENTO DI LETTERE E BENI CULTURALIIT-CE0103UBL63CONS Ve 352caEssere re e non essere re100735UNICAMPANIA02628oam 2200745I 450 991070961670332120180612110006.0(CKB)5470000002472073(OCoLC)761382490(OCoLC)995470000002472073(EXLCZ)99547000000247207320111115j198501 ua 0engurun||||a|a||txtrdacontentcrdamediacrrdacarrierAerothermal tests of a 12.5° cone at Mach 6.7 for various Reynolds numbers, angles of attack, and nose shapes /Robert J. Nowak, Cindy W. Albertson, and L. Roane HuntWashington, D.C. :National Aeronautics and Space Administration, Scientific and Technical Information Branch,January 1985.1 online resource (87 pages) illustrationsNASA/TP ;2345"January 1985."Prepared at Langley Research Center.Includes bibliographical references (pages 19-21).Flow distributionnasatConesnasatAerodynamic heatingnasatBoundary layer transitionnasatTurbulent boundary layernasatAngle of attack (Aerodynamics)Noses (Aircraft)Reynolds numberAerothermodynamicsAerothermodynamicsfastAngle of attack (Aerodynamics)fastNoses (Aircraft)fastReynolds numberfastFlow distribution.Cones.Aerodynamic heating.Boundary layer transition.Turbulent boundary layer.Angle of attack (Aerodynamics)Noses (Aircraft)Reynolds number.Aerothermodynamics.Aerothermodynamics.Angle of attack (Aerodynamics)Noses (Aircraft)Reynolds number.Nowak Robert J.1401795Albertson Cindy W.Hunt L. Roane(Lewis Roane),United States.National Aeronautics and Space Administration.Scientific and Technical Information Branch,OCLCEOCLCEOCLCQOCLCFOCLCOOCLCQGPOBOOK9910709616703321Aerothermal tests of a 12.5° cone at Mach 6.7 for various Reynolds numbers, angles of attack, and nose shapes3470994UNINA