Untersuchungen zur Interferenz von Zelle zu Antrieb bei hoher Unterschallstroemung

SIGLECopy held by FIZ Karlsruhe; available from UB/TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Untersuchungen zum laminar-turbulenten Umschlag der Grenzschicht

SIGLECopy held by FIZ Karlsruhe; available from UB/TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Ultralight aeroplanes: How quiet can they be?

SIGLECopy held by FIZ Karlsruhe; available from UB/TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Hubschrauber-Laermforschung

SIGLECopy held by FIZ Karlsruhe; available from UB/TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Leistungsvermessung von Fluegelprofilen

SIGLECopy held by FIZ Karlsruhe; available from UB/TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Untersuchungen zur Interferenz von Zelle zu Antrieb bei Ultra-Hochbypass-Triebwerken

SIGLECopy held by FIZ Karlsruhe; available from UB/TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Beschaffung des aerodynamischen Optimierungsverfahren von JAMESON MEGAFLOW Sachbericht

SIGLEAvailable from TIB Hannover: DtF QN1(44,43) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekBundesministerium fuer Bildung, Wissenschaft, Forschung und Technologie, Bonn (Germany)DEGerman

Erzeugung eines Oberflaechenmodells fuer die VFW 614

A surface model of the VFW 614 is developed and serves to investigate by means of panel methods the flow around the aircraft and in particular the region between engine, pylon, wing and fuselage. As this region requires very fine discretization, other aircraft components are greatly simplified to obtain reasonable central processing unit times. The engine jet is simulated by the internal nacelle flow. The panel model, a half model, comprises source panels for the aircraft surface, dipole panels for the engine intake, and the Kutta panels at the wing and fan nacelle trailing edges, as well as two vortex models for the wing and for the fan nacelle. The discretization of the fuselage is condensed near the wings. The wing is generated together with the adjacent fuselage sections. Measured values from flight tests are available for the flight Mach number and the pressure distribution on the outer surface of the fan nacelle. (orig.)Available from TIB Hannover: RN 4165(1994,31) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEDEGerman

Investigation of a semi-implicit multigrid method for reacting flows

Numeric flow simulations shown their capabilities mainly for flows without chemical reactions. Here a code for simulation of 1D reacting flows has been investigated. It is based on a semi-implicit time discretization scheme and uses upwind spatial discretization and a full multigrid method. Especially, the Jacobian matrix and its inversion have been examined. Code modifications have been implemented in order to check the accuracy of the numerical results. Programming numeric process to check the analytic elements of the source Jacobian matrix was the most notable occupation of the investigation, hence it has been described in details within present report. Coding errors have been corrected and the modifications have been checked. There is now no uncertainty left about the numerical results obtained after this check. However, for computations of reacting mixtures of air and hydrogen the improved code needs some empirical correction factor in the implicit part of the scheme in order to obtain converged solutions. It is speculated that the convergence problems have their origin in the errors of operator splitting and linearization which make the scheme first order accurate in time. (orig.)Study performed at ENSIMEV (Valenciennes)Available from TIB Hannover: RN 4165(1995,2) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEDEGerman

Ein flugmechanisches Verfahren zur Berechnung von Fernfeldinterferenzen infolge von Modellhalterungen an Flugzeugmodellen im Windkanal

Available from TIB Hannover: RO 8051(94,11) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEDEGerman