360/spl deg/ PSP measurements in transonic flow

Integrated surface pressure distribution measurements using the PSP technique on a three-dimensional aircraft model with a number of various flaps, rudders and ailerons were performed at angles of attack between -4/spl deg/ to 36/spl deg/, angles of sideslip between -13/spl deg/ to 13/spl deg/ for Mach numbers from 0.6 to 0.95. In such cases, if the pressure distribution around the model is determined, forces and moments can be calculated. In addition comparisons with conventional balance techniques are possible. The main challenge to get good PSP results on one hand is the arrangement of hardware, components of model illumination and camera observation - especially in the handling of eight simultaneously operating CCD cameras. On the other hand the software should be able to handle in a short time all the necessary synchronization between the PSP-system and wind tunnel, all PSP images, correction of lens errors, model deformation etc.. This paper describes how these problems are solved. A large number of results were mainly obtained on the AerMacchi M346 trainer aircraft model in May 2000 in the DNW-HST at Amsterdam.

[1]  J. Callis,et al.  Surface pressure field mapping using luminescent coatings , 1993 .

[2]  Martin Morris,et al.  Aerodynamic applications of pressure sensitive paint , 1993 .

[3]  James H. Bell,et al.  Image registration for luminescent paint applications , 1993 .

[4]  A. Vollan,et al.  A new optical pressure measurement system (OPMS) , 1991, ICIASF '91 Record., International Congress on Instrumentation in Aerospace Simulation Facilities.

[5]  R. H. Engler,et al.  Aerodynamic assessment of an optical pressure measurement system (OPMS) by comparison with conventional pressure measurements in a high speed wind tunnel , 1991, ICIASF '91 Record., International Congress on Instrumentation in Aerospace Simulation Facilities.

[6]  Wim Ruyten,et al.  On the Effects of Reflected Light in Luminescent Paint Measurements , 2000 .

[7]  Vladimir Evguenyevich Mosharov,et al.  Set of luminescence pressure sensors for aerospace research , 1993 .

[8]  R. H. Engler,et al.  DLR PSP system intensity and lifetime measurements , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[9]  C. Klein.  Einsatz einer druckempfindlichen Beschichtung (PSP) zur Bestimmung des momentanen Druckfeldes von Modellen im Windkanal , 1997 .

[10]  M. Sellers.  Application of pressure sensitive paint for determining aerodynamic loads on a scale model of the F-16C , 2000 .

[11]  R. H. Engler.  Further developments of pressure sensitive paint (OPMS) for non flat models in steady transonic flow and unsteady conditions , 1995, ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.