The Research and Technology Organization (RTO) of NATO. Educational Notes AC/323(AVT-186)TP/338, 2010, 434 pp. - ISBN 978-92-837-0121-7
Papers presented at the AVT-186 RTO AVT/VKI Lecture Series held at the von Karman Institute, Rhode St. Genese, Belgium, 29 March - 1 April 2010.
The Lecture Series focus on the presentation of ground testing methodologies and facilities as well as the numerical tools currently involved for the design of aerospace vehicles. The course addressed four main points: simulation methodologies and capabilities of hypervelocity facilities; their operation and main applications for re-entry vehicle design; the measurement techniques applied for these reacting high speed flows; and the CFD tools dedicated to the design of high enthalpy facilities and those mostly used for the investigations of aerothermodynamic phenomena.
All the lecturers are well recognized in their field of expertise and succeed to share at best their large experience through detailed presentations and lecture notes.
Hypersonic ground testing simulation is first presented, including real gas effect. Typical capabilities and limitations are discussed for high enthalpy facilities. Their operations and applications are illustrated with NASA Ames EAST and Ballistic facilities, CUBRC expansion tubes, ITAM impulse wind tunnels and DLR HEG shock tunnel. Fast response probes and unsteady measurement techniques are exposed as well as non-intrusive diagnostic tools, like spectroscopy from VUV to NIR, and thermal imaging. Their contribution for aerothermodynamic database and reference test case are also reported.
The use of numerical tools is presented, in a first step, with their utilization for the design of high enthalpy facilities and the corresponding predictions of performances. In a second step the coupling approach between experimental and numerical investigations, typical of hypersonic research, is shown for the specific case of HEG facility. Finally the current CFD challenges regarding aerothermodynamic simulation and validation for planetary re-entry studies is exposed.Contents.
Preface.
Ground Testing for Hypervelocity Flow, Capabilities and Limitations. - (Hornung, H.G.).
The LENS Facilities and Experimental Studies to Evaluate the Modeling of Boundary Layer Transition, Shock/Boundary Layer Interaction, Real Gas, Radiation and Plasma Phenomena in Contemporary CFD Codes. - (Holder, M.S.).
Selected Achievements and Discoveries Made in High-Enthalpy Flow Facilities. - (Hornung, H.G.).
Shock Tube and Ballistic Range Facilities at NASA Ames Research Center. - (Grinstead, J.H.; Wilder, M.C.; Reda, D.C.; Cornelison, C.J.; Cruden, B.A.; Bogdanoff, D.W.).
Experimental Studies of Radiation and Plasma Effects behind the Incident Shock in LENS XX, and the Unsteady Flow Characteristics Associated with "Free Flight" Shroud and Stage Separation and Mode Switching in LENS II. - (Holden, M.S.).
Advanced Spectroscopic and Thermal Imaging Instrumentation for Shock Tube and Ballistic Range Facilities. - (Grinstead, J.H.; Wilder, M.C.; Reda, D.C.; Cruden, B.A.; Bogdanoff, D.W.).
Measurement Techniques for Flow Diagnostic in ITAM Impulse and Wind Tunnels. -(Kharitonov, A.M.).
A Closely Coupled Experimental and Numerical Approach for Hypersonic and High Enthalpy Flow Investigations Utilising the HEG Shock Tunnel and the DLR TAU Code. - (Hannemann, K; Martinez Schramm, J.; Wagner, A.; Karl, S.; Hannemann, V.).
CFD Tools for Design and Simulation of Transient Flows in Hypersonic Facilities. - (Jacobs, P.A.; Gollan, R.J.; Potter, D.F.; Gildfind, D.E.; Eichmann, T.N.; O'Flaherty, B.F.; Buttsworth, D.R.).
Modeling of High-Velocity Flows in ITAM Impulse Facilities. - (Kharitonov, A.M.).
Challenges to Computational Aerothermodynamic Simulation and Validation for Planetary Entry Vehicle Analysis. - (Gnoffo, P.A.; Johnston, CO.; Kleb, В.).
