SAE ARP 5905-2003 Calibration and Acceptance of Icing Wind Tunnels《结冰风洞的校准和验收》.pdf

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3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497

4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP5905 AEROSPACE RECOMMENDED PRACTICE ARP5905 Issued 2003-09 Reaffirmed 2015-09

5、Calibration and Acceptance of Icing Wind Tunnels RATIONALE ARP5905 has been reaffirmed to comply with the SAE five-year review policy. TABLE OF CONTENTS 1. SCOPE 4 1.1 Background4 1.2 Purpose4 1.3 Facility/Site Qualification5 2. APPLICABLE DOCUMENTS.5 2.1 SAE Publications5 2.2 U.S. Government Public

6、ations .6 2.3 Non-U.S. Government Publications .6 3. SYMBOLS7 4. FACILITY DESCRIPTION13 4.1 Example Closed-Circuit Facility .14 4.2 Open-Circuit Wind Tunnel Considerations.15 5. FACILITY PERFORMANCE TARGETS 16 6. INSTRUMENTATION.18 6.1 Facility Instrumentation 18 6.2 Calibration Instrumentation 22 7

7、. FACILITY CALIBRATION 26 7.1 Baseline Calibration .27 7.2 Interim Calibration27 7.3 Check Calibration.27 7.4 Ice Shape Continuity Check.28 8. CALIBRATION PROCEDURES.28 8.1 Aero-thermal Calibration 28 8.2 Icing Cloud Calibration.31 9. ACCEPTANCE CRITERIA.37 9.1 Aerodynamic 37 9.2 Icing Cloud .38 10.

8、 CALIBRATION AND ACCEPTANCE REPORT .38 10.1 Aerodynamic Calibration38 10.2 Icing Cloud Calibration.38 10.3 Test Facility Qualification Statement39 11. NOTES.39 APPENDIX A LIQUID WATER CONTENT MEASUREMENT METHODS .40 APPENDIX B WATER QUALITY, DROPLET FREEZE-OUT, AND DROPLET SUPERCOOLING.54 APPENDIX C

9、 GUIDELINE TO DETERMINING DERIVED AERODYNAMIC PARAMETERS.55 APPENDIX D EXAMPLE OF A FACILITY LIQUID WATER CONTENT CALIBRATION 66 APPENDIX E NOZZLE WATER FLOW CALIBRATION PROCEDURE .73 FIGURE 1 Example of Typical Closed-Circuit, Refrigerated Icing Tunnel .14 FIGURE 2 Example of a Refrigerated Non-rec

10、irculating Icing Wind Tunnel15 FIGURE 3 Example of Total Temperature Probe 19 FIGURE 4 Example of Total Pressure Probe 20 FIGURE 5 Example of Static Pressure Probe .21 FIGURE 6 Example of Pressure/Temperature Calibration Rake.23 FIGURE 7 Example of Hot Wire Anemometer Instrumentation Probe.24 FIGURE

11、 8 Example of Icing Cloud Calibration Grid 26 FIGURE 9 Example of Centerline Static Pressure Correction Data 30 FIGURE 10 Example of Icing Cloud Uniformity and Size Data35 FIGURE 11 Facility Droplet Size Calibration .36 FIGURE A1 Example of Icing Calibration Blade 40 FIGURE A2 Icing Blade Collection

12、 Efficiency 42 FIGURE A3 Cylinder Collection Efficiency.47 FIGURE C1 Cone Probe 64 FIGURE D1 KA Versus Air Pressure Plot68 FIGURE D2 KV Versus Airspeed Plot .69 FIGURE D3 Comparison of Measured to Calculated LWC 72 SAE INTERNATIONAL ARP5905 2 OF 76TABLE 1 Test Section Performance Targets.16 TABLE 2A

13、 Minimum Test Matrix for Aerodynamic Calibration.29 TABLE 2B Minimum Test Matrix for Thermodynamic Calibration29 TABLE A1 Ludlam Limit LWC (g/m3) for a 0.25 cm (0.1 in) Diameter Cylinder .48 TABLE D1 Test Points To Determine KA .67 TABLE D2 Test Points To Determine KV .69 TABLE D3 Test Points To Inv

14、estigate MVD Effect.71 TABLE E1 Flow Coefficient Test Conditions, Mod-1 Spray Nozzles .74 TABLE E2 Flow Coefficient Test Conditions, Standard Spray Nozzles .74 TABLE E3 Example of Nozzle Record.76 SAE INTERNATIONAL ARP5905 3 OF 761. SCOPE: This SAE Aerospace Recommended Practice (ARP) document provi

15、des recommended practices for the calibration and acceptance of icing wind tunnels to be used in testing of aircraft components and systems and for the development of simulated ice shapes. This document is not applicable to air-breathing propulsion test facilities configured for the purposes of engi

16、ne icing tests. Use of facilities as part of an aircrafts ice protection Certification Plan should be reviewed and accepted by the applicable regulatory agency prior to testing. Following acceptance of a test plan, data generated in these facilities may be submitted to regulatory agencies for use in

17、 the certification of aircraft ice protection systems and components. Certain types of tests may be appropriate in facilities with capabilities that are not as rigorously characterized as by the practices defined herein, and the acceptability of these tests should be coordinated with the applicable

18、regulatory agency. 1.1 Background: The U.S. Federal Aviation Administration established an icing plan in 1997 to respond to a need for a comprehensive program to create an awareness of inflight icing issues and to establish documents to provide training and guidance for regulatory authorities, aircr

19、aft operators, research organizations, and aircraft manufacturers. The FAA published a 14-task plan, entitled the FAA Inflight Aircraft Icing Plan, and identified groups of people within the U.S. Government and throughout the aircraft industry to address the action items contained in this plan. Task

20、 11 of this plan called for the development of validation criteria and data for simulation methods used to determine ice shapes on aircraft. It also indicated that this task was to include data on wind tunnels, ice accretion computer codes, and icing tankers. The FAA suggested a coordinated effort a

21、mong research organizations, industry, and regulatory authorities and individuals were asked to participate in this work. Task 11 was divided into three subtasks and the people that participated in Subtask A were tasked with addressing criteria for the use of tankers, tunnels, and codes. Three docum

22、ents were developed by the members of the Task 11.A Working Group and these three documents are being published as SAE ARPs. While each document follows a format that is appropriate to the topic, the three documents provide guidance for the application of codes (ARP5903), tankers (ARP5904), and tunn

23、els (ARP5905) to the icing certification or qualification process. 1.2 Purpose: The purpose of this ARP is to compile in one definitive source, commonly accepted calibration and acceptance criteria and procedures for icing wind tunnels. Wind tunnels that meet these criteria will have known icing con

24、ditions simulation capability. Each manufacturer is responsible for obtaining regulatory agency approval for using a specific facility to generate certification data in their specific certification program. SAE INTERNATIONAL ARP5905 4 OF 761.2 (Continued): The reader is directed to the following: DO

25、T/FAA/CT-88/8-2, Aircraft Icing Handbook, Volume 2, Chapter V, Section 4.0, Testing to Demonstrate Compliance, March 1991; Aircraft Ice Protection, U.S. Department of Transportation, Federal Aviation Administration, Advisory Circular (AC) 20-73, April 21, 1971; Certification of Transport Category Ro

26、torcraft, (AC 29-2C), September 30, 1999; and the advisory circulars for icing certification of airplanes (AC 23.1419-2A and AC 25.1419-1) for the myriad of considerations that are inherent in defining and conducting test programs for the purpose of obtaining certification for flight into known icin

27、g conditions. This ARP provides recommended practices for the calibration of icing wind tunnels. It is not intended to substitute for the regulatory agencys latitude in selecting the combination of tests or inspections required to demonstrate compliance with regulations as described in the Aircraft

28、Icing Handbook. 1.3 Facility/Site Qualification: An icing facility that conforms to the recommended practices in this document provides an artificial icing test volume consistent with the capability provided by current wind tunnel technology. If results produced in a test facility are to be used in

29、the certification process of aircraft components or ice protection systems, it should be substantiated that the facility calibration and supporting resources conform to this ARP. Also, a comparison between the facility icing condition envelopes that can be simulated and those defined by the regulato

30、ry authorities should be presented. 2. APPLICABLE DOCUMENTS: The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase o

31、rder. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1 SAE Publications: Available from S

32、AE, 400 Commonwealth Drive, Warrendale, PA 15096-0001. 2.1.1 AIR5504, Aircraft Inflight Icing Terminology 2.1.2 AIR5906, Ice Shape Measurement and Comparison Techniques Workshop 2.1.3 ARP5904, Airborne Icing Tankers 2.1.4 ARP5905, Calibration and Acceptance of Icing Wind Tunnels SAE INTERNATIONAL AR

33、P5905 5 OF 762.1.5 AIR5320. Summary of Icing Simulation Test Facilities 2.1.6 AIR4906, Droplet Sizing Instrumentation Used in Icing Facilities 2.2 U.S. Government Publications: FAA Reports: Documents with numbers such as DOT/FAA/AR-00/37 or DOT/FAA/CT-88/8-3 are available through the National Techni

34、cal Information Service (NTIS), Springfield VA. FAA regulations are available from: Superintendent of Documents, U.S. Government Printing Office, Mail Stop SSOP, Washington, DC 20402-0001. FAA Advisory Circulars are available from: U.S. Department of Transportation, Subsequent Distribution Office, S

35、VC-121.23, Ardmore East Business Center, 3341 Q 75th Avenue, Landover, MD 20785. 2.2.1 Aircraft Icing Handbook, Volume 2, Chapter V, Section 4.0 Testing to Demonstrate Compliance, DOT/FAA/CT-88/8-2, March 1991. 2.2.2 Ide, R. F., Liquid Water Content and Droplet Size Calibration of the NASA Lewis Ici

36、ng Research Tunnel, NASA Technical Memorandum TM-102447, Jan. 1990. 2.2.3 Equations, Tables and Charts for Compressible Flow,“ NASA Ames Research Center, Moffett Field, California, Report No. NACA 1135, 1953. 2.2.4 Advisory Circular (AC) 20-73, Aircraft Ice Protection, U.S. Department of Transportat

37、ion, Federal Aviation Administration, April 21, 1971. 2.2.5 Advisory Circular (AC) 23.1419-2A, Certification of Part 23 Airplanes for Flight in Icing Conditions, U.S. Department of Transportation, Federal Aviation Administration, August 19, 1998. 2.2.6 Advisory Circular (AC) 25.1419-1, Certification

38、 of Transport Category Airplanes for Flight in Icing Conditions, U.S. Department of Transportation, Federal Aviation Administration, August 18, 1999. 2.3 Non-U.S. Government Publications: 2.3.1 Jose C. Gonsalez and E. Allen Arrington, Monroe R. Curry, Aero-Thermal Calibration of the NASA Glenn Icing

39、 Research Tunnel (2000 Tests), American Institute of Aeronautics and Astronautics Paper # AIAA-2001-0233. 2.3.2 Quality Assessment for Wind Tunnel Testing, AGARD Advisory Report No. 304, July, 1994. 2.3.3 Assessment of Wind Tunnel Data Uncertainty, AIAA Standard S-071-1995, May, 1995. SAE INTERNATIO

40、NAL ARP5905 6 OF 762.3.4 Coleman, W.H and W.G. Steele, Jr., Experimentation and Uncertainty Analysis for Engineers, John Wiley National Research Council, Canada; Servizio di Taratura in Italy; etc.) and should be calibrated at least annually or in accordance with each facility-operator organizations

41、 processes and procedures. 6.1 Facility Instrumentation: Standard instruments to measure desired speed/velocity and temperature conditions in the test section should be used. This will enable the tunnel operator to vary the drive motor rotation speed to maintain the velocity within the set velocity

42、tolerance limits. The following sections provide information on the minimum instrumentation set for measuring tunnel total pressure, static pressure, and total temperature. Special care should be used in the selection of the instrumentation for an icing tunnel due to the icing conditions that will e

43、xist. Typically, heated probes are used to prevent icing. 6.1.1 Tunnel Temperatures: Two types of tunnel temperatures are commonly used in icing tunnels. Total temperatures are generally measured and used in the calculation of the velocity of the tunnel while static temperatures are used as the defi

44、ning temperature for icing conditions. Static temperatures are calculated values derived from the measurement of total temperature, total pressure, and static pressure, and calculated Mach number using Equations C1 and C2, from Appendix C. 6.1.2 Total Temperature Probe: A total temperature probe is

45、commonly located in the settling chamber near Station 1 of Figure 1, that is, downstream of the heat exchanger and the turning vanes of the tunnels fourth corner, but upstream of the spray bars. If the probe is of the enclosed, heated type, as shown in Figure 3, then it must be aspirated to minimize

46、 measurement errors due to the heating system. If the probes sensing resistance temperature device (RTD) or thermistor is naturally ventilated by the airflow in the settling chamber, then sufficient airflow must be present to minimize self heating. Because of this need for ventilation or aspiration,

47、 a recovery error correction should be applied to the measured temperature to convert it to total temperature. SAE INTERNATIONAL ARP5905 18 OF 76FIGURE 3 - Examle of Total Temperature Probe 6.1.3 Tunnel Pressures: Two types of pressure measurements are required for determining the velocity of the te

48、st section: (1) total pressure and (2) static pressure. Individual total and static pressure probes or a combined pitot-static probe may be used for pressure measurements. Aircraft type probes, similar to that shown in Figure 4, are generally used. SAE INTERNATIONAL ARP5905 19 OF 76FIGURE 4 - Exampl

49、e of Total Pressure Probe 6.1.4 Total Pressure: Total pressure, PTU, may be measured in the settling chamber immediately upstream of the test section but downstream of the atomizing spray bars (Station 2 in Figure 1) using a total pressure probe (Figure 4) or upstream of the test article in the constant area of the test section (Station 3 in Figure 1) using a pitot-static probe, in accordance with st