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.

Problems for Analysis.- Flow over a Slender Cone.- Problem 2: Turbulent Base Flow.- Problem 3: Flow over a 2D Ramp.- Problem 4: Flow over a 3D Obstacle.- Problem 5: Corner Flow.- Problem 6: Double (Simple) Ellipsoid.- Problem 7: Flow over a Delta Wing.- Problem 8: Non-equilibrium Flow in an Arc Jet or a Shock Tube.- Appendix: Non-equilibrium Model for Problem 6.- Problems 1-2.- Hypersonic Boundary Layer and Base Flow.- Computation of Hypersonic Turbulent Flow over a Rearward Facing Step.- Hypersonic Cone Flow Predictions Using an Implicit Upwind Space-Marching Code.- Synthesis A Synthesis of Results for Test Cases 1 and 2: Hypersonic Boundary Layer and Base Flow.- Problems 3-4.- Experiments on Shock-Wave/Boundary-Layer Interactions Produced by Two-Dimensional Ramps and Three-Dimensional Obstacles.- An Experimental Contribution to the Flat Plate 2D Compression Ramp, Shock/Boundary Layer Interaction Problem at Mach 14: Test Case 3.7.- Viscous, 2-D, Laminar Hypersonic Flows over Compression Ramps.- Computational Results for 2-D and 3-D Ramp Flows with an Upwind Navier-Stokes Solver.- Application of the Galerkin/Least-Squares Formulation to the Analysis of Hypersonic Flows: I. Flow over a Two-Dimensional Ramp.- The Application of an Adaptive Upwind Unstructured Grid Solution Algorithm to the Simulation of Compressible Laminar Viscous Flows over Compression Corners.- Computation of Flows over 2D Ramps.- Hypersonic Viscous Flow over Two-Dimensional Ramps.- Grid-Refinement Study of Hypersonic Laminar Flow over a 2-D Ramp.- Contribution to Problem 3 Using a Galerkin Least Square Finite Element Method.- Computational Results for Flows over Compression Ramps.- Implicit Upwind Finite-Difference Simulation of Laminar Hypersonic Flow over a 2D Ramp.- Synthesis A Synthesis of Results on the Calculation of Flow over a 2D Ramp and a 3D Obstacle: Antibes Test Cases 3 and 4.- Problem 5.- Experimental Study of the Longitudinal Hypersonic Corner Flow Field.- Problem 6.- 6.1 Non-reacting Flows.- Experimental Study of the Flow Around a Double Ellipsoid Configuration.- Solution of the Euler Equations Around a Double Ellipsoidal Shape Using Unstructured Meshes and Including Real Gas Effects.- Computation of 2D Inviscid Hypersonic Flows Using Unstructured Polygonal Meshes.- An Upwind Relaxation Method for Hypersonic Viscous Flows over a Double-Ellipsoidal Body.- Navier-Stokes Calculations over a Double Ellipse and a Double Ellipsoid by an Implicit Non-centered Method.- Application of the Galerkin/Least-Squares Formulation to the Analysis of Hypersonic Flows: II. Flow Past a Double Ellipse.- The Application of an Adaptive Unstructured Grid Method to the Solution of Hypersonic Flows Past Double Ellipse and Double Ellipsoid Configurations.- Computation of the Hypersonic Flow over a Double Ellipsoid.- High Resolution Schemes for Steady Hypersonic Flow.- Numerical Simulation of Laminar Hypersonic Flow Past a Double-Ellipsoid.- Inviscid and Viscous Flow Calculation over a Double Ellipse with an Implicit Centered Method.- 2D Hypersonic Viscous Flow Past a Double Ellipse Geometry.- Hypersonic Flows over a Double or Simple Ellipse.- Solving Flow Equations for High Mach Numbers on Overlapping Grids.- An Explicit Finite-Difference Solution of Hypersonic Flows Using Rational Runge-Kutta Scheme.- Viscous and Inviscid Hypersonic Flow About a Double Ellipsoid.- Numerical Simulation of Hypersonic Flow over a Double Ellipse Using a Taylor-Galerkin Finite Element Formulation with Adaptive Grids.- Hypersonic Viscous Flow Past Double Ellipse and Past Double Ellipsoid - Numerical Results.- Adaptive Mesh Embedding for Reentry Flow Problems.- Synthesis Attempt to Evaluate the Computation for Test Case 6.1-Cold Hypersonic Flow Past Ellipsoidal Shapes.- 6.2/6.3 Reacting Flows.- A Staggered Mesh Finite Difference Scheme for the Computation of Hypersonic Euler Flows.- Reactive Flow Computations by Upwind Finite Elements.- Numerical Analysis of Chemically Reacting Inviscid Flow in 2-D.- A Contribution to the Prediction of Hypersonic Non-equilibrium Flows.- Reactive and Inert Inviscid Flow Solutions by Quasi-linear Formulations and Shock Fitting.- Inviscid Calculations by an Upwind Finite Element Method of Hypersonic Flows over a Double (Single) Ellipse.- Contribution to Problem 6 Using an Upwind Euler Solver with Unstructured Meshes.- Inviscid Hypersonic Flow Simulations Using an Explicit Scheme.- Computation of Thermochemical Non-equilibrium Flows Around a Simple and a Double Ellipse.- Synthesis Some Comments on the Numerical Computations of Reacting Flows over the Double-Ellipse (Double Ellipsoid).- 6.4 Rarefied Flows.- DSMC Calculations for the Double Ellipse.- Rarefied Flow Around a Double Ellipse.- The Hypersonic Double Ellipse in Rarefied Flow.- Problem 7.- 7.1 Vortex Flows.- Leeside Flow over Delta Wing at M = 7.15 Experimental Results for Test Case 7.1.2*.- Hypersonic Delta Wing Flow Calculations Using a Multidomain MUSCL Euler Solver.- Finite Volume 3DNS and PNS Solutions of Hypersonic Viscous Flow Around a Delta Wing Using Osher's Flux Difference Splitting.- Inviscid Hypersonic Flow over a Delta Wing.- Hypersonic Leeside Delta-Wing-Flow Computations Using Centered Schemes.- Synthesis Evaluation of Contributions for Test Cases 7.1.1 and 7.1.2.- 7.2 Rarefied Flows.- Experimental Density Flowfields over a Delta Wing Located in Rarefied Hypersonic Flows.- Experiments on the Heat Transfer and on the Aerodynamic Coefficients of a Delta Wing in Rarefied Hypersonic Flows.- DSMC Calculations for the Delta Wing.- Rarefied Gas Flow Around a 3D-Deltawing.- Synthesis (Problems 6.4/7.2) Appraisal of the Rarefied Flow Computations.- Problem 8.- Study of a Nitrogen D.C. Plasma Torch at Different Pressures Using Optical and Thermal Diagnostics.- Non-equilibrium Flow in an Arc-Jet.- Non-equilibrium Flow in an Arc Heated Wind Tunnel.- Calculation of Non-equilibrium Flows in a High-Enthalpy Wind Tunnel.- Application of Program LAURA to Thermochemical Non-equilibrium Flow Through a Nozzle.- Non-equilibrium Flow in a Hypersonic Wind Tunnel Nozzle.- Non-equilibrium Flow in a Hypersonic Wind Tunnel Nozzle.- Quasi Monodimensional Inviscid Non-equilibrium Nozzle Flow Computation.- Synthesis Non-equilibrium Flow in an Arcjet or a Shock Tube.- Conclusion.- General Synthesis.- Index of Contributors.