LE MEMOIRE SUIVANT S'INSCRIT DANS LE CADRE DE LA MODELISATION DE LA PHASE DE RENTREE D'UN AVION SPATIAL DANS L'ATMOSPHERE. SON OBJET EST D'ETUDIER L'ECOULEMENT D'AIR A TRES HAUTE ENTHALPIE LE LONG DU CORPS DE RENTREE. LA MODELISATION PROPOSEE PREND EN COMPTE LES EFFETS DE NON-EQUILIBRE VIBRATIONNEL ET CHIMIQUE ET PROPOSE UNE METHODE ORIGINALE DE COUPLAGE. TROIS ETUDES NUMERIQUES SONT ENSUITE PRESENTEES ET CONCERNENT: 1) LES ONDES DE CHOC DROITES MONODIMENSIONNELLES; 2) LES TUYERES BIDIMENSIONNELLES; 3) LES OBSTACLES BIDIMENSIONNELS. CES DIFFERENTES SITUATIONS METTENT EN EVIDENCE L'INFLUENCE DE LA PRISE EN COMPTE DES EFFET DE NON-EQUILIBRE SUR LES GRANDEURS MACROSCOPIQUES DE L'ECOULEMENT. LA METHODE NUMERIQUE UTILISEE POUR LES CALCULS BIDIMENSIONNELS EST DE TYPE VOLUMES-FINIS, ON UTILISE UNE DECOMPOSITION EN FLUX DE VAN-LEER. ON UTILISE UNE METHODE DE SOUS-RELAXATION POUR TRAITER LES TERMES DE PRODUCTION D'ESPECES

This entry describes the experimental work conducted in the Department of Aeronautics at Imperial College in connection with Test Problems 1 and 2 of the "Workshop on Hypersonic Flows for Reentry Problems, Part I". These are defined as follows: Test Problem 1 Flow Over a Slender Cone Test Problem 2 Turbulent Base Flow The main requirement of this text is to present the experimental data for direct comparison with the predictions of CFD codes. We have therefore concentrated mainly on a factual statement of measuring techniques and results, together with an assessment of experimental accuracy. Future publications will be devoted to more extensive physical interpretations and discussions of the results. We have produced a large volume of data, some of which were categorised as "MANDATORY" and some as "OPTIONAL" for the purposes of CFD validation. However, only the "MANDATORY" data are presented here, although the other data are available and will be published separately later. 2. EXPERIMENTAL ARRANGEMENT 2. 1 The Test Facility The experiments were conducted in the Imperial College No. 2 Gun tunnel. This facility is a conventional intermittent blowdown tunnel with a contoured Mach 9 (nominal) axisymmetric nozzle fed by a free piston compression heater. The operating condition under which the data contained in this report were obtained is presented in Table 1. Test 2 T (oK) M b. Mlm Po (N/m ) Re/m T (oK) IX) IX) Case IX) w 1. 1 7 7 +0. 14 9. 16 6. 67x10 5. 5xl0 59.

ON ETUDIE DES ECOULEMENTS HYPERSONIQUES EULERIENS EN DESEQUILIBRE THERMODYNAMIQUE, POUR LESQUELS ON PRESENTE DES EQUATIONS D'EULER, DE BILAN D'ESPECES ET DE RELAXATION VIBRATIONNELLE. ON MODELISE LES PROCESSUS D'ECHANGES VIBRATIONNELS LORS DES COLLISIONS ENTRE MOLECULES ET ON EXPOSE UN MODELE DE COUPLAGE ENTRE LA DISSOCIATION DES MOLECULES ET LEUR RELAXATION VIBRATIONNELLE. EN RAISON DU CARACTERE HYPERBOLIQUE ET ELLIPTIQUE DU SYSTEME D'EQUATIONS, ON UTILISE UNE METHODE NUMERIQUE PSEUDO-INSTATIONNAIRE. LE SYSTEME D'EQUATIONS EST ALORS RESOLU PAR UNE METHODE DE VOLUMES-FINIS SEMI-IMPLICITE, OU LES FLUX SONT DECOMPOSES SELON UNE TECHNIQUE DE VAN-LEER ET POUR LESQUELS ON UTILISE LA NOTION DE GAMMA-EQUIVALENT. LES MODELES PHYSIQUES ET NUMERIQUES PRESENTES ICI, SONT TESTES SUR DEUX TYPES D'ECOULEMENTS, L'UN EN TUYERE, L'AUTRE AUTOUR D'UN CORPS EMOUSSE; DES COMPARAISONS SONT FAITES ENTRE LES RESULTATS OBTENUS AVEC LES DIFFERENTES ETAPES DE LA MODELISATION. ENFIN, LE CODE DE CALCUL A ETE VECTORISE ET PARALLELISE ET ON PRESENTE DES COMPARAISONS DE TEMPS CPU ET DE TEMPS DE RESTITUTION OBTENUS DANS LES DIFFERENTES VERSIONS

Because of the growing interest in hypersonic flows, the AGARD Fluid Dynamics Panel initiated a sub-working group on instrumentation for hypersonics in 1989. This sub-group, chaired by J. WENDT (VKI -Belgium), was composed of: A. BOUTIER (ONERA -France), K. BUTEFISCH (DLR -Germany), R. CATTOLICA (SANDIA Lab. -USA), V. CLINE (AEDC -USA), A. GIRARD (ONERA -France), R. McKENZIE (NASA Ames -USA), S. OCHELTREE (NASA Langley -USA) and G. SMEETS (ISL -Franco-German Inst.). As a result of several meetings, the idea came to organize this workshop, 27th April - 1st May 1992, on "New Trends in Instrumentation for Hypersonic Research", at Le Fauga-Mauzac ONERA center, in France, where the new hot-shot arc-heated facility F4, as well as a new conference building, were recently completed. This workshop has been organized in close connection with the AGARD FDP Symposium to be held in Torino 4 - 8 May 1992 on "Theoretical and Experimental Methods in Hypersonic Flows": the main conclusions and ideas expressed by the papers and during the discussions of this workshop are reported in session 7 and have been presented in Torino in a special Instrumentation session. As chairman of this workshop, I express many thanks to the Organizing Committee composed of Karl BUTEFISCH, Andre GIRARD, Stewart OCHELTREE and John WENDT for their very constructive help, leading to a meeting that was recognized to be very fruitful for all the participants.

Shock wave research covers important inderdisciplinary areas which range from basic topics on gasdynamics, combustion and detonation, physico-chemistry of high temperature gases, plasma physics, astro and geophysics, materials science, astronautics and space technology to medical and industrial applications. This book includes 202 papers presented at the 18th the International Symposium on Shock Waves which describe the research frontier of shock wave phenopmena and 14 plenary lectures which show the state of the art of various fields of shock wave research. This proceedings is a unique collection of most important and updated shock wave research.

Volume 2 of this significant work presents previously unpublished cutting-edge lectures from the Third French-Russian Workshop on Fluid Dynamics held in Tashkent in April 1995. Reflecting the Workshop?s main themes, this book particularly focuses on: expermental investigation of unsteady separated flow, 3D configurations, laminar and transitional flows, turbulent shock, shock interaction in hypersonic flow, pressure pulsation in separated flows and jets and high enthalpy flows using wind tunnels. modeling of free surface flows, natural gas combustion, vortical gas flows and acoustic processes in complex channels, non-equilibrium hypersonic viscous flows, wall law for fluids and compressible fluid jets with vortex zones. theoretical predictions of aerodynamic performances with analyses of supersonic combustion, detonation, and sumulation of reactive mixing layer. solution methods for quasilinear parabolic equations and other calculations including incompressible Navier Stokes equations and parabolic equations by Monte-Carlo methods. numerical algorithms for the simulation of atmospheric gas dynamics, kinetic schemes for viscous gas dynamic flows and evolutionary algorithms for complex optimization problems. This book will be of particular interest to all engineers and research scientists in Fluid Dynamics, Aeronautics, Aerospace and Mechanical or Applied Mathematics.

Recently, there have been significant advances in the fields of high-enthalpy hypersonic flows, high-temperature gas physics, and chemistry shock propagation in various media, industrial and medical applications of shock waves, and shock-tube technology. This series contains all the papers and lectures of the 19th International Symposium on Shock Waves held in Marseille in 1993. They will be published in four topical volumes, each containing papers on related topics, and preceded by an overview written by a leading international expert. The volumes may be purchased independently.