NASA Technical Memorandum 4632 USAATCOM Technical Report 94-A-011 ¢, 2-D and 3-D Oscillating Wing Aerodynamics for a Range of Angles of Attack Including Stall R. A. Piziali (NASA-T_-4632) 2-D ANt 3-0 N95-19119 OSCILLATING WING AEROOY_AMICS FOR A RANGE _F ANGLES GF ATTACK INCLUDING STALL (NASA. Apes Research Center) Unclas September 1994 570 p H1/02 0037906 V National Aeronautics and US Army Space Administration Aviation and Troop Command NASA Technical Memorandum 4632 USAATCOM Technical Report 94-A-011 2-D and 3-D Oscillating Wing Aerodynamics for a Range of Angles of Attack Including Stall R. A. Piziali, Aeroflightdynamics Directorate, U.S. Army Aviation and Troop Command, Ames Research Center, Moffett Field, California September 1994 National Aeronautics and US Army Space Administration Aviation and Troop Command Ames Research Center Aeroflightdynamics Directorate Moffett Field, CA 94035-1000 Moffett Field, CA 94035-1000 CONTENTS Page LIST OF TABLES ................................................................................................................................................. V LIST OF FIGURES ............................................................................................................................................... vi SUMMARY ........................................................................................................................................................... INTRODUCTION ................................................................................................................................................. NOMENCLATURE .............................................................................................................................................. TEST DESCRIPTION ........................................................................................................................................... 2 Facility ............................................................................................................................................................ 2 Model .............................................................................................................................................................. 3 Wing ........................................................................................................................................................ 3 Tip caps ................................................................................................................................................... 3 Boundary layer trip .................................................................................................................................. 3 Location of the pressure taps ................................................................................................................... 3 Installation ...................................................................................................................................................... 3 3-D configuration .................................................................................................................................... 3 2-D configuration .................................................................................................................................... 3 Oscillating drive mechanism ................................................................................................................... 4 Splitter plates (2-D and 3-D) ................................................................................................................... 4 Instrumentation ............................................................................................................................................... 4 Pressure transducers ................................................................................................................................ 4 Angle of attack ........................................................................................................................................ 4 Oscillation frequency ............................................................................................................................... 4 Wing temperature .................................................................................................................................... 4 Wind tunnel operating parameters ........................................................................................................... 4 Data Acquisition ............................................................................................................................................. 4 Hardware ................................................................................................................................................. 4 Dynamic data acquired ............................................................................................................................ 4 Static data acquired ................................................................................................................................. 5 Data acquisition process .......................................................................................................................... 5 Filtering ................................................................................................................................................... 5 Data storage ............................................................................................................................................. 5 Acquisition software ............................................................................................................................... 5 Data Reduction ............................................................................................................................................... 5 Test Procedures ............................................................................................................................................... 6 Calibrations ............................................................................................................................................. 6 Zeros ........................................................................................................................................................ 7 Pitch oscillation test ................................................................................................................................. 7 Steady-state test ....................................................................................................................................... 7 Quasi-steady test ..................................................................................................................................... 7 2-D test .................................................................................................................................................... 7 Micro-tuft surface flow visualization ...................................................................................................... 7 Steady-boundary value measurements .................................................................................................... 8 Dynamic pressure survey ........................................................................................................................ 8 Steady-state wake measurements ............................................................................................................ 8 iii PAGK BLANK NOT FILMFJ9 TestConditions...............................................................................................................................................8 Primaryoperatingconditions..................................................................................................................8 Pitchoscillationtest.................................................................................................................................8 Steady-statetest.......................................................................................................................................8 Quasi-steadytest.....................................................................................................................................8 Micro-tuftsurfaceflowvisualization......................................................................................................9 Steady-boundaryvaluemeasurements....................................................................................................9 Dynamicpressuresurvey........................................................................................................................9 Steady-statewakemeasurements............................................................................................................9 DISCUSSION........................................................................................................................................................9 ExperimentalAccuracy..................................................................................................................................9 Model.......................................................................................................................................................9 Pressuretransducers................................................................................................................................9 Angleofattack........................................................................................................................................9