AIAA R-093-2003 Calibration of Subsonic and Transonic Wind Tunnels《亚音速和跨音速流动状态》.pdf

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1、AIAA R-093-2003 Calibration of Subsonic and Transonic Wind Tunnels AIAA R-093-2003 Recommended Practice Calibration of Subsonic and Transonic Wind Tunnels Sponsor American Institute of Aeronautics and Astronautics Abstract The calibration of a wind tunnel is a necessary, yet often neglected, process

2、 needed to ensure accurate and repeatable test data. In general, a wind tunnel calibration program encompasses many related topics-basic operating condition calibration, flow quality mapping, wall interference, and model blockage corrections are all topics that can be addressed as part of a tunnel c

3、alibration program. However, it is not practical to address all of these topics in a single document, so the scope of this recommended practice has been defined as the empty test section calibration of subsonic and transonic wind tunnels. This American Institute of Aeronautics and Astronautics (AIAA

4、) Recommended Practice is intended to (1) provide an overview on the calibration of subsonic and transonic wind tunnels and (2) provide a basis for commonality within the wind tunnel community in the area of wind tunnel calibration. This document is a compilation of input from several wind tunnel op

5、erators and users that summarizes the best practices and recommendations from these experts. AlAA R-093-2003 Library of Congress Cataloging-in-Publication Data Recommended practice : calibration of subsonic and transonic wind tunnels. Includes bibliographical references and index. ISBN 1-56347-661-4

6、 (Hardcopy) - ISBN 1-56347-662-2 (Electronic) 1. Wind tunnels-Calibration. 2. Aerodynamics-Research-Standards. 3. Wind tunnel models-Testing-Standards. I. American Institute of Aeronautics and Astronautics. p. cm. TL567.W5R435 2003 629.13452-dc22 2003023502 Published by American Institute of Aeronau

7、tics and Astronautics 1801 Alexander Bell Drive, Reston VA 20191 Copyright O 2003 American Institute of Aeronautics and Astronaut i cs All rights reserved. No part of this publication may be reproduced in any form, in electronic retrieval system or otherwise, without prior written permission of the

8、publisher. Printed in the United States of America. II AlAA R-093-2003 Contents . Foreword . viii 1 2 2.1 2.2 3 3.1 3.2 3.3 3.3.1 3.3.2 3.3.3 3.3.4 3.4 3.5 3.6 3.6.1 3.6.2 3.6.3 4 4.1 4.1.1 4.1.2 4.1.3 4.2 4.2.1 4.2.2 4.2.3 4.3 4.3.1 4.3.2 4.3.3 4.4 4.5 4.5.1 Executive summary . 1 Introduction 3 Bac

9、kground . 3 Definitions . 4 Wind tunnel calibration requirements and objectives 5 Cali brat ion basics 5 Calibration goals . 7 Types of calibrations . 9 Full calibrations . 9 Check calibrations 11 Axial static pressure distribution . 11 Integrated upflow calibration . 11 Calibration parameters 11 .

10、Frequency of calibration 12 Establishing statistical process control in the wind tunnel calibration 13 Check standard . 14 Historical tracking 14 Out-of-control variations 15 Calibration and flow field measurements 16 Steady-state pressure measurements 17 Calibration measurements 17 Mapping test sec

11、tion steady-pressure distributions 18 Recommendations on data acquisition . 19 Axial static pressure distribution measurements . 20 Static pressure pipe 20 Other stationary axial static pressure measurement devices 23 Translating probes 24 Flow-angularity measurements . 25 Integrated upflow measurem

12、ent 25 Pressure probes for flow-angle measurement 26 Nonpressure probe systems . 28 Temperature measurements . 29 Humidity and dew point measurements 29 Fog chamber unit 30 . AlAA R-093-2003 4.5.2 4.5.3 4.5.4 5 5.1 5.1.1 5.1.2 5.1.3 5.2 5.3 5.4 5.4.1 5.4.2 6 Annexes A B C c . 1 c.2 c.2.1 c.2.2 C.2.3

13、 c.3 c.4 c.5 C.5.1 C.5.2 c.5.3 c.5.4 C.6 D D.l D.2 D.3 D.4 Chilled mirror instruments . 30 Aluminum oxide sensors . 30 Silicon sensors 31 Calibration test planning and execution 32 Pretest preparation . 33 Planning and reporting 33 33 Online data analysis requirements 34 Test preparation and executi

14、on . 36 Data analysis and data corrections . 39 Post-test activities 40 Reporting of results . 40 Followup activities . 41 Examples of calibration procedures 42 Uncertainty analysis in the planning phase . Nomenclature . 43 Additional information on pressure probes used for flow-angle measurement 51

15、 Calibration of NASA Glenn Research Centers 9- by i5-Foot Low-Speed Wind Tunnel . 55 Description of facility . 55 Ca I i b rat io n hardware . 57 Tunnel and test section instrumentation . 57 Calibration hardware and instrumentation . 58 Data acquisition systems 63 Detailed calibration procedure 63 F

16、requency and duration of full and check calibrations 66 Data analysis 66 Flow field data . 66 Turbulence measurements . 67 Boundary layer rake data 68 Calibration curves for determining test section operating conditions 69 Reporting of results . 73 Lockheed Martin Low Speed Wind Tunnel . 75 Descript

17、ion of facility 75 Test conditions 76 Flow quality and calibration goals and requirements . 76 Tunnel and calibration instrumentation/hardware description . 77 . iv AlAA R-093-2003 D.5 Airstream calibration procedure 78 D.6 Data reduction 79 D.7 Frequency and duration of full and check calibrations

18、80 D.8 Data acquisition system 81 D.9 Data analysis and data corrections . 81 D.l O Flow quality information 81 D.ll Reporting of results 82 . D.12 E E.l E.2 E.3 E.3.1 E.3.2 E.3.3 E.4 E.5 E51 E.5.2 E.5.3 E.5.4 E.6 E.6.1 E.6.2 E.7 E.7.1 E.7.2 E.7.2.1 E.7.2.1 E.7.2.3 E.7.3 Recommendations for future c

19、alibrations 82 Calibration of the 11- by 1 I-Foot Transonic Wind Tunnel at the NASA Ames Research Center 85 Overview of the facility calibration and flow quality surveys 85 Facility description 85 Facility tunnel conditions. hardware. and instrumentation . 86 Static and total pressure . 86 Tunnel to

20、tal temperature . 88 Specific humidity . 88 Facility calibration goals 88 Facility calibration installation and instrumentation . 88 Static pipe installation . 88 Static pipe instrumentation 89 Flow uniformity installation 90 Flow uniformity instrumentation 91 Data acquisition 91 Static pipe data ac

21、quisition . 92 Flow uniformity data acquisition 92 Data reduction 92 Calibration equations 92 Flow uniformity equations . 93 Local A-plane and B-plane flow angle . 93 Total temperature 94 Boundary layer . 94 Data reduction methods for the static pipe 94 . . . E.7.4 Data reduction methods for the flo

22、w uniformity . 95 E.8 Calibration results . 95 E.8.1 Factors affecting the static pipe calibration results 95 E.8.1.1 Temporal variation of test section flow 95 E.8.1.2 Effects of test section slots 97 V AlAA R-093-2003 E.8.1.3 Mounting interference effects . 97 E.8.1.4 Tap error and pipe joint effe

23、cts 98 E.8.1.5 Instrumentation error effects 99 E.8.2 E.8.2.1 E.8.2.2 E.8.2.3 E.8.3 E.8.3.1 E.8.3.2 E.8.3.3 E.8.3.4 F F.l F.l.l F.1.2 F.1.3 F.2 F.2.1 F2.2 F.3 F.3.1 F.3.2 F.4 F.5 G G . 1 G.2 G.3 G.4 G.5 G.6 G.7 G.8 G.8.1 Calibration results for the static pipe . 99 Mach number effects 99 Reynolds nu

24、mber effects 99 Centerline versus 33 in . below centerline 1 o1 Calibration results for the flow uniformity 102 Flow angle . 102 Total pressure . 102 Total temperature 103 Boundary layer 104 Maintenance calibration of the Veridian 8-Foot Transonic Wind Tunnel . 105 Description of facility . 105 Faci

25、lity description 105 Resident tunnel instrumentation 106 Data acquisition systems 107 Calibration hardware and instrumentation . 108 Static pipe 108 Instrumentation 108 Maintenance calibration description 109 Test section installation . 109 . Test procedures 112 Frequency and duration of full and ch

26、eck calibrations 113 Data reduction and analyses . 114 Mach number calibration of the Arnold Engineering Development Center PWT 164 Transonic Tunnel (16T) with the High-Angle Automated Sting (HAAS) test section 121 Introduction . 121 Description of facility . 121 Cali brat ion hardware 121 Calibrati

27、on instrumentation . 123 Test free-stream conditions 123 Test procedures 124 Data uncertainty 124 Results and discussion . 124 Centerline Mach number distributions 124 . vi AlAA R-093-2003 G.8.1 .I HAAS strut interference . 125 G.8.1.2 Test region . . 126 G.8.1.3 Axial Mach number gradient . 126 G.8

28、.2 Mach number calibration . 128 G.8.2.1 Baseline calibration . . 128 G.8.2.2 Reynolds number effects . . 128 G. 8.3 H Cal i b rat on a pp I i cat io n method o1 og y 128 Bibliography of subsonic and transonic tunnel calibration reports . 131 References . . 132 vii AIAA R-093-2003 Foreword Wind tunn

29、els are the primary source of test data for basic aerodynamic research and for the design and development of aircraft, aircraft components (including propulsion systems), launch vehicles and land vehicles. Since the 1960s, tens of thousands of wind tunnel test hours have usually been required to com

30、plete the development and evaluation of a new aircraft. Because of the advances in instrumentation and data systems that provide more accurate measurement of flow parameters and because of the increased sensitivity of aerodynamic and propulsion system performance to wind tunnel flow quality, the acc

31、urate calibration of wind tunnels has become progressively more important. Without detailed knowledge of the wind tunnel operating conditions and flow quality, it is impossible to provide reliable and accurate test data to support the needs of test customers. In the past, there have been workshops a

32、nd general meetings to discuss issues pertaining to wind tunnel calibration, but in general, no closure or final recommendations were produced from these exercises. To provide a means of closure on calibration issues, the AIAA Ground Testing Technical Committee (GTTC) formed a working group on wind

33、tunnel calibration methodology. This working group was chartered to bring together wind tunnel calibration experts from various Government, industry, and university organizations to share information on calibration techniques and to ultimately make recommendations on preferred methods for wind tunne

34、l calibration. Because of the large variance in wind tunnel characteristics across facilities (e.g., Mach number range, size and type of facility, types of testing, model blockage effects, etc.), an exhaustive treatment of all pertinent calibration issues was not practical. Therefore, the working gr

35、oup focused on a subset of wind tunnels and test ranges. On the basis of discussions with wind tunnel users and operators from within the GTTC, the scope of the Wind Tunnel Calibration Methodology Working Group was limited to the empty test section calibration of subsonic and transonic wind tunnels.

36、 For this exercise, subsonic wind tunnels have a test section Mach number capability up to 0.5, and transonic tunnels up to 1.5. The working group decided to classify this document as a Recommended Practice because the variety of wind tunnels and types of testing conducted in each tunnel make it dif

37、ficult to define standards that can be directly applied in all instances. Instead, general recommendations are made on hardware, methodologies, and philosophy such that each reader can determine the best calibration program for his or her situation. This document does not address such issues as wall

38、 interference, support interference, or model size. This is not to minimize the importance of these issues, since they must be addressed for each proposed wind tunnel test. However, many of these issues are covered in detail in other reference documents. In order to facilitate the exchange of inform

39、ation between the member organizations and to build a database on wind tunnel calibrations, each organization wrote a summary report on their calibration procedures. The information in these summary reports became the building blocks for constructing this Recommended Practice. The members of the GTT

40、C Wind Tunnel Calibration Methodology Working Group were Allen Arrington, Chairman QSS Group, Inc., at the NASA Glenn Research Center Mark Perry, Vice-Chair Stephen Arnette Alan Boone Colin Britcher Old Dominion University Lockheed Martin Corporation Sverd ru p Technology NASA Ames Research Center T

41、om Beutner Air Force Research Lab Andy Garrell Veridian Engineering Division viii AIAA R-093-2003 James Hallissy Dennis Hergert Bonnie Johnson Mark Kammeyer Mike Mills Mark Rennie David Sanford Lew Scherer Frank Steinle NASA Langley Research Center The Boeing Company National Institute for Aviation

42、Research The Boeing Company Sverdrup Technology, AEDC Group Aiolos Engineering Corp. Micro Craft Technology Northrop Grumman Sverdrup Technology, AEDC Group James Thain National Research Council, Canada On the recommendation of the Wind Tunnel Calibration Working Group the following knowledgeable in

43、dividuals reviewed the document and provided valuable critique: Max Amaya Cabot Broughton Peter Brown Joel Everhart Brian Geppart Jose Gonsalez Michael Hemsch Frank Jackson Frank Kmak Alan Linne Kevin Mejia Scott Meredith Roman Paryz Fred Peitzman Juergen Quest Mathew Rueger David Spera NASA Ames Re

44、search Center National Research Council, Canada QSS Group, Inc., at the NASA Glenn Research Center NASA Langley Research Center University of Washington QSS Group, Inc., at the NASA Glenn Research Center NASA Langley Research Center Sverdrup Technology, AEDC Group NASA Ames Research Center NASA Glen

45、n Research Center The Boeing Company Sverd ru p Technology Veridian Northrop Grumman European Transonic Wind Tunnel The Boeing Company QSS Group, Inc., at the NASA Glenn Research Center Peter Waudby-Smith Aiolos Engineering This document was approved by the AIAA Ground Test Technical Committee (Mr.

46、Allen Arrington, chairman) in January 2003. The AIAA Standards Executive Council (Mr. Phil Cheney, chairman) approved the document in September 2003. ix AIAA R-093-2003 The AIAA Standards Procedures dictates that all approved Standards, Recommended Practices, and Guides are advisory only. Their use

47、by anyone engaged in industry or trade is entirely voluntary. There is no agreement to adhere to any AIAA standards publication and no commitment to conform to or be guided by standards reports. In formulating, revising, and approving standards publications, the committees on standards will not cons

48、ider patents that may apply to the subject matter. Prospective users of the publications are responsible for protecting themselves against liability for infringement of patents or copyright or both. Acknowledgments The working group chair acknowledges the following significant contributions by nonwo

49、rking group members: Max Amaya (NASA Ames Research Center) for providing a tunnel calibration example on the Ames 11- by Il-Foot Transonic Wind Tunnel (Annex E), and Nancy Amman (InDyne, Inc., at NASA Glenn) for her editorial review of the draft document and for her considerable aid in making a lot of pieces into one cohesive document. Dedication The Wind Tunnel Calibration Working Group dedicates this document in memory of Frank Wright, formerly of the Boeing Company. Frank was not only an original member of the working group, but was also among those originally consulted on the fo