S8  Engenharia Aeroespacial    Titulo: HYPERSONIC LAMINAR BOUNDARY LAYERS WITH ADIABATIC WALL CONDITION   Resumo : ABSTRACT. A NEW SET OF SELF-SIMILAR SOLUTIONS OF A COMPRESSIBLE LAMINAR BOUNDARY LAYER IS USED FOR AIR AS PERFECT GAS AND WHERE THE VISCOSITY IS A POWER FUNCTION OF TEMPERATURE. MODIFIED LEVY-MANGLER AND DORODNITSYN-HOWARTH TRANSFORMATIONS ARE PRESENTED TO SOLVE THE FLOW IN A THIN LAMINAR BOUNDARY LAYER WITH NO EXTERNAL PRESSURE GRADIENTS ON A SMOOTH FLAT PLATE. THIS RESULT IN AN EXPLICIT RELATION BETWEEN THE STREAM FUNCTION AND THE ENTHALPY FIELDS DESCRIBED BY A CLOSED-COUPLED SYSTEM OF NONLINEAR ORDINARY DIFFERENTIAL EQUATIONS. IN THE PRESENT WORK, BOUNDARY LAYER FLOWS WITH EXTERNAL MACH NUMBERS 4 AND 10 OVER IN ADIABATIC WALL ARE STUDIED. THE PRESENT SOLUTION METHODOLOGY PROVIDES A STRAIGHTFORWARD WAY OF COMPARING RESULTS USING THE VISCOSITY-TEMPERATURE LINEAR RELATION, SUTHERLAND LAW, AND THE RELATION ACCORDING TO THE KINETIC THEORY. ALSO, THE RESULTS MAY PROVIDE IMPORTANT DATA NEEDED FOR THE DESIGN OF FUTURE HYPERSONIC VEHICLES. KEYWORDS: SELF-SIMILAR EQUATIONS, COMPRESSIBLE LAMINAR BOUNDARY LAYER, SUPERSONIC AND HYPERSONIC FLOWS.     Autores : Myrabo, Leik N. Nagamatsu, Henry T. Rusak , Z 0 Toro, Paulo G. de P.     Trabalho Completo :   COBEM99 | Comissão  Organizadora | Palestras | Sessões Técnicas | Autor | Simpósios e Sessões Especiais | Revisores |  Título  dos  Trabalhos | Local