Literature Review: Application of the Pressure Sensitive Paint ...
14th Int Symp on Applications of Laser Techniques to Fluid Mechanics Lisbon, Portugal, 07-10 July, 2008
Application of the Pressure Sensitive Paint Technique to a Scramjet Nozzle Flow in the DLR Hypersonic Wind Tunnel Walter H. Beck1, Ulrich Henne1, Christian Hirschen2 German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, 1: Experimental Methods Department, Bunsenstrasse 10, 37073 Göttingen, Germany. [email protected] 2: Wind Tunnel Department, Linder Höhe, 51147 Cologne, Germany. [email protected]
Abstract The Pressure Sensitive Paint Technique has been successfully applied to a measurement of surface pressures on two different Scramjet nozzles in a Mach 7 flow of the Hypersonic Wind Tunnel H2K of the DLR in Cologne. The agreement with results from pressure taps is very good. Physical insights into the flow phenomena could be obtained, and an optimization of the gas injection into the nozzle plenum chamber could be carried out. The influence of surface temperature gradients was assessed, as were error sources discussed. The utilization of PSP on a large, industry-scale wind tunnel was carried out successfully, pointing the way for the longer term aim of applying PSP to flows of much shorter duration, such as in the High Enthalpy Shock Tunnel HEG of the DLR in Göttingen.
1. Introduction The Pressure Sensitive Paint (PSP) technique has found wide acceptance in carrying out measurements of surface pressure distributions in low speed, transonic, supersonic and cryogenic flows, and in rotating machinery (e.g. turbines); a good overview is given in [1]. There have been some applications to hypersonic flows, as discussed in [1], and presented in, for example, [2-5]. These applications of the PSP technique are generally made more difficult, however, by the high and spatially non-uniform surface temperatures which can exist, and/or also by the short test times available; in a high enthalpy shock tunnel at 20 MJ/kg, for example, test times can be
Application of the Pressure Sensitive Paint Technique to a Scramjet Nozzle Flow in the DLR Hypersonic Wind Tunnel Walter H. Beck1, Ulrich Henne1, Christian Hirschen2 German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, 1: Experimental Methods Department, Bunsenstrasse 10, 37073 Göttingen, Germany. [email protected] 2: Wind Tunnel Department, Linder Höhe, 51147 Cologne, Germany. [email protected]
Abstract The Pressure Sensitive Paint Technique has been successfully applied to a measurement of surface pressures on two different Scramjet nozzles in a Mach 7 flow of the Hypersonic Wind Tunnel H2K of the DLR in Cologne. The agreement with results from pressure taps is very good. Physical insights into the flow phenomena could be obtained, and an optimization of the gas injection into the nozzle plenum chamber could be carried out. The influence of surface temperature gradients was assessed, as were error sources discussed. The utilization of PSP on a large, industry-scale wind tunnel was carried out successfully, pointing the way for the longer term aim of applying PSP to flows of much shorter duration, such as in the High Enthalpy Shock Tunnel HEG of the DLR in Göttingen.
1. Introduction The Pressure Sensitive Paint (PSP) technique has found wide acceptance in carrying out measurements of surface pressure distributions in low speed, transonic, supersonic and cryogenic flows, and in rotating machinery (e.g. turbines); a good overview is given in [1]. There have been some applications to hypersonic flows, as discussed in [1], and presented in, for example, [2-5]. These applications of the PSP technique are generally made more difficult, however, by the high and spatially non-uniform surface temperatures which can exist, and/or also by the short test times available; in a high enthalpy shock tunnel at 20 MJ/kg, for example, test times can be
