European Transonic Windtunnel Advanced Measurement Techniques at High Reynolds Number Testing in the European Transonic Windtunnel

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1 Advanced Measurement Techniques at High Reynolds Number Testing in the April 2005 Aerospace Testing Expo 1

2 EUROPEAN TRANSONIC WINDTUNNEL GmbH Köln-Porz Germany CRYOGENIC TEMPERATURES and MODERATE PRESSURE INCREASE Flight Reynolds Number Testing Advanced Measurement Techniques at High Reynolds Number Testing in the Capability April 2005 Aerospace Testing Expo 2

3 Temperature Range 310 K > 110 K N u m b e r Pressure Range 115 kpa > 450 kpa o l d s Mach Number Range 0.15 > 1.30 Test Section 2.4 m x 2.0 m April 2005 Aerospace Testing Expo 3

4 STANDARD MEASUREMENT TOOLS N u m b e r o l d s Strain Gauge Balances Incidence Measurement Units Pressure Scanners SINCE 10 YEARS IN OPERATION April 2005 Aerospace Testing Expo 4

5 ADVANCED MEASUREMENT TECHNIQUES Wing Deformation Measurement N u m b e r Temperature and Pressure Sensitive Paint o l d s Flow Visualization and Measurement April 2005 Aerospace Testing Expo 5

6 Independent Variation of Tunnel Parameters Pseudo Reynolds Number Effects Ambient Temperature Facilities Pt Re Pure Reynolds Number Variation Pt Aeroelastic Effect at const Re Pt Re Re April 2005 Aerospace Testing Expo 6

7 Wing Deformation Measurement 0,4 M ReC Pt Tt Q Alpha (Mio) (kpa) (K) (kpa) [ ] ,2 -C p 0,0-0,2 Twist -0,4 Unloaded Wing Bent Wing under load -0,6 0,0 0,2 0,4 0,6 0,8 1,0 1,2 1,4 Twist and Bending April 2005 Aerospace Testing Expo 7

8 Stereo Pattern Tracking System Half Models upstream downstream April 2005 Aerospace Testing Expo 8

9 Application of Markers at Half Span Model LETRASET Markers: - Circular dots, approx. 15 pixels in diameter - More markers near wing tip to compensate for chord length - Good contrast to background April 2005 Aerospace Testing Expo 9

10 Wing Twist and Bending Measurements Twist 1.2 deg Bend 42 mm Lift Lift April 2005 Aerospace Testing Expo 10

11 Calibration Frame for Full Span Models April 2005 Aerospace Testing Expo 11

12 Temperature and Pressure Sensitive Paint TSP PSP April 2005 Aerospace Testing Expo 12

13 Transition Detection by Temperature Sensitive Paint April 2005 Aerospace Testing Expo 13

14 Transition Detection by Temperature Sensitive Paint First step for future PSP Verify Required Equipment Investigate Handling and Tools April 2005 Aerospace Testing Expo 14

15 Development of Transition with Reynolds Number Ma = CL = 0.5 Re = 6 Mio April Mio 12 Mio Aerospace Testing Expo 17 Mio 15

16 Pressure Sensitive Paint First Check-Out in Pilot Facility PETW 2d Profile PSP Camera and Flash Light April 2005 Aerospace Testing Expo 16

17 PSP - PETW Check-Out Oxygen Injection Capabilities Control Stability of different Oxygen Concentration Acquisition of Images at different Test Conditions Check-out of TSP Equipment Test Preparation and Handling T tot =230K, P tot =120 kpa, Ma=0.79 April 2005 Aerospace Testing Expo 17

18 Pressure Sensitive Paint First Test in ETW April 2005 Aerospace Testing Expo 18

19 PSP - First Test in ETW in October 2004 Oxygen Vapourizer during Operation 0.5 Nm³/sec Oxygen Pipeline in Tunnel Building April 2005 Aerospace Testing Expo 19

20 PSP - First Test in ETW in October 2004 First successful test in ETW 300 K 160 K up to 340 kpa Oxygen Injection with manual control Stabilisation of Oxygen Level at requested amounts of 700, 1000 and 1500 ppm Images successfully acquired Surface roughness of paint 0.3μm April 2005 Aerospace Testing Expo 20

21 Flow Visualisation and Measurement Doppler Global Velocimetry Laser Light Sheet Background Oriented Schlieren April 2005 Aerospace Testing Expo 21

22 LASER Systems require Seeding ETW - wind tunnel without particles Seeding with ice particle below 240 K April 2005 Aerospace Testing Expo 22

23 Wake Measurement - DGV System MDAW Project April 2005 Aerospace Testing Expo 23

24 Laser Light Sheet Background Oriented Schlieren Reynolds Number Influence on Wake Vortex Position LUFO - AIRWI April 2005 Aerospace Testing Expo 24

25 Laser Light Sheet (LLS) 1 Light Sheet 2 Observation cameras flow o2 o1 LS Region of Interest April 2005 Aerospace Testing Expo 25

26 Background Oriented Schlieren (BOS) flow Speckles Plates April 2005 Aerospace Testing Expo 26

27 Further Development Pressure Sensitive Paint for cryogenic conditions Standard operation of optical systems for Model Deformation Measurement Flow Visualization Testing tools for Aeroelastic Investigations April 2005 Aerospace Testing Expo 27

28 Importance of FLIGHT REYNOLDS NUMBER TESTING demonstrated High Standard on TESTING TECHNIQUES achieved Further Improvement on PRODUCTIVITY and COST EFFICIENCY April 2005 Aerospace Testing Expo 28

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