Application of Temperature and Pressure Sensitive Paints to DLR Hypersonic Facilities: “lessons learned”

PSP and TSP measurements have been carried out on the following DLR facilities: small test shock tube, High Enthalpy Shock Tunnel (both in Gottingen) and the Hypersonic Wind Tunnel (in Cologne). Based on the results from these measurements, various challenges and problem areas could be identified: the role played by these in hindering a quantitative application of PSP/TSP to the facilities is discussed, and ways and means are presented for either overcoming them or at least ameliorating their influence.

[1]  U. Henne,et al.  Investigation of three-dimensional dynamic stall on an airfoil using fast-response pressure-sensitive paint , 2014, Experiments in Fluids.

[2]  T. V. Jones,et al.  Heat-transfer measurements in short-duration hypersonic facilities , 1973 .

[3]  Tianshu Liu,et al.  Pressure and Temperature Sensitive Paints , 2004, Experimental Fluid Mechanics.

[4]  Christian Klein,et al.  Pressure sensitive paint systems for pressure distribution measurements in wind tunnels and turbomachines , 2000 .

[5]  Ulrich Henne,et al.  Development of PSP Technique for Application on the VFE-2 65° Delta Wing Configuration , 2006 .

[6]  W. Cook,et al.  Reduction of data from thin-film heat-transfer gages - A concise numerical technique. , 1966 .

[7]  Christian Klein,et al.  Experimental Investigation of the Effect of Forward-facing Steps on Boundary Layer Transition , 2015 .

[8]  C. Klein,et al.  Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel , 2005 .

[9]  G. Eitelberg,et al.  Shock Tube Tests , 1997 .

[10]  Stefan Hein,et al.  Complementary Numerical and Experimental Data Analysis of the ETW Telfona Pathfinder Wing Transition Tests , 2011 .

[11]  Tianshu Liu,et al.  Fast Pressure-Sensitive Paint for Flow and Acoustic Diagnostics , 2014 .

[12]  Keisuke Asai,et al.  Global Heat Transfer Measurement in a Hypersonic Shock Tunnel Using Temperature-Sensitive Paint , 2003 .

[13]  Ulrich Henne,et al.  Nonadiabatic Surface Effects on Transition Measurements Using Temperature-Sensitive Paints , 2015 .

[14]  Ali Gülhan,et al.  Analysis of jet in cross flow interaction with different investigation techniques , 2013 .

[15]  F.-J. Niezgodka.  Der Hyperschallwindkanal H2K des DLR in Köln-Porz (Stand 2000) , 2002 .

[16]  Klaus Hannemann,et al.  Recent Extensions to the High Enthalpy Shock Tunnel Göttingen (HEG , 2008 .