1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2017 SAE International All rights reserved. No part of this p
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:/standards.sae.org/AIR1703A AEROSPACE INFORMATION REPORT AIR1703 REV. A Issued 1985-11 Revised 2012-12 Reaffirmed
5、2017-12 Superseding AIR1703 In-Flight Thrust Determination RATIONALE AIR1703A has been reaffirmed to comply with the SAE Five-Year Review policy. FOREWORD The popularity of SAE AIR1703, In-Flight Thrust Determination, as a resource for guiding and standardizing the approaches to aircraft propulsion
6、system in-flight thrust determination led the E-33 committee in 1996 to assess the validity of the practices set forth in the 1985 document. The committee determined that while the information contained in the document was still valid, there had been sufficient development of technology and changes
7、in practice to warrant a revision to the original document. While the spirit and intent of the original document have been retained, it has been reorganized by reconvened Subcommittee E-33A to improve the flow of the material for a first-time reader, sections have been rewritten to provide clarity,
8、and the figures have been scrutinized to assure that they support the textual material, are accurate, and are properly labeled. In addition, case studies are included within the appendices to illustrate how the principles and guidelines of this document have been employed. A brief history of the E-3
9、3 committee is given in Appendix A. TABLE OF CONTENTS 1. SCOPE 8 1.1 Purpose . 8 1.2 Limitations . 9 1.3 Overview . 9 1.3.1 Program Planning Guidelines (Section 3) . 9 1.3.2 Definitions and Methodology (Section 4) 9 1.3.3 Propulsion System Installations (Section 5) 10 1.3.4 In-Flight Thrust Methods
10、(Section 6) . 10 1.3.5 Calibration Techniques (Section 7) . 10 1.3.6 Test Data Acquisition Systems (Section 8) . 10 1.3.7 Analysis and Validation of Thrust Determination (Section 9) 11 1.3.8 Appendices . 11 2. REFERENCES 12 2.1 Applicable Documents 12 2.1.1 Section 1 . 12 2.1.2 Section 4 . 12 2.1.3
11、Section 6 . 12 2.1.4 Section 7 . 13 2.1.5 Section 8 . 14 2.1.6 Section 9 . 15 2.2 Symbols 16 3. PROGRAM PLANNING GUIDELINES . 20 3.1 Administration . 21 3.1.1 Working Group 21 3.1.2 Responsibilities . 21 3.1.3 Expectations 21 3.1.4 Benchmark 21 3.1.5 Budget . 22 3.1.6 Compliance . 22 3.1.7 Schedule
12、. 22 3.2 Planning 22 3.2.1 Component Test 23 3.2.2 Engine Test . 23 3.2.3 Flight Test . 23 3.2.4 Meetings 24 3.2.5 Documentation 24 3.2.6 Accuracy . 24 3.2.7 Risk Mitigation . 24 3.2.8 Schedule Tracking 24 3.3 Technical . 24 3.3.1 Thrust/Drag Accounting 24 3.3.2 Engine Analysis . 25 3.3.3 Aircraft A
13、nalysis 25 3.3.4 Methodologies . 25 3.3.5 Instrumentation . 26 3.3.6 Data Type 26 3.3.7 Uncertainty Analysis 26 3.3.8 Data Acquisition 26 3.4 Development . 26 3.4.1 Data Reduction . 27 3.4.2 Test Data Analysis 27 3.4.3 Data Quality Checks . 28 3.4.4 Stabilization Time 28 3.4.5 Update Engine Models 2
14、8 SAE INTERNATIONAL AIR1703A Page 2 of 316_ 3.4.6 Update Aircraft Models 28 3.4.7 Update Uncertainty . 29 3.5 Reporting . 29 3.5.1 Component Tests 29 3.5.2 Engine Tests . 29 3.5.3 Flight Tests 29 3.5.4 Maintenance of the Working Group 29 3.5.5 Problem Resolution . 29 3.5.6 Lessons Learned . 29 4. DE
15、FINITIONS AND METHODOLOGY . 30 4.1 Thrust 30 4.1.1 Single-Stream Engine Thrust 31 4.1.2 Dual-Stream Engine Thrust: . 38 4.1.3 Selected Equations for Reference 40 4.1.4 Thrust/Drag Bookkeeping System 41 4.1.5 Installed Thrust 41 4.2 Thrust/Drag Accounting 42 4.2.1 Inlet Force Increment 44 4.2.2 Exhau
16、st-System Force Increment . 47 4.2.3 Trim Force Increment 48 4.3 Ideal Thrust and Normalized Groups 48 4.3.1 Ideal Nozzle 48 4.3.2 Non-dimensional Groups 48 4.4 Nozzle Coefficients . 49 4.4.1 Flow Coefficient, CD50 4.4.2 Specific Thrust Coefficients, VC and XC . 52 4.4.3 Gross Thrust Coefficient, GC
17、 . 53 4.5 Vectoring Considerations 54 5. PROPULSION SYSTEM INSTALLATIONS 55 5.1 Nacelle Installations 55 5.1.1 Turbojet Nacelles 56 5.1.2 Long-Duct Turbofan Nacelles . 57 5.1.3 Intermediate or Short-Duct Turbofan Nacelles . 57 5.2 Integrated Installations 57 5.2.1 Secondary Flows . 61 5.2.2 Inlet Co
18、nsiderations 61 5.2.3 Nozzle/Afterbody Considerations 62 5.2.4 Ejector Installations . 63 6. IN-FLIGHT THRUST METHODS 64 6.1 Overall Performance Method 65 6.2 Gas-Path/Nozzle Methods 67 6.2.1 Mass Flow Determination 69 6.2.2 Nozzle Thrust Determination 70 6.2.3 External Flow Effects 76 6.2.4 Residua
19、l Error Procedure (RERR) 77 6.3 Computer Model/Data Match Procedures . 81 6.4 Nozzle Exit Traverse Method 83 6.4.1 Rake Design and Installation 83 6.4.2 Data Analysis 84 6.5 Trunnion Method . 85 6.6 Example Applications of In-Flight Thrust Methods . 87 6.6.1 Single-Spool Fixed-Nozzle Turbojet . 87 6
20、.6.2 Single-Exhaust Turbofan. 89 6.6.3 Separate-Stream Turbofan . 93 6.6.4 Mixed-Flow Afterburning Turbofan 94 SAE INTERNATIONAL AIR1703A Page 3 of 316_ 6.6.5 Example of the Use of Multiple In-flight Thrust Methods 96 6.6.6 In-flight Thrust Calculation Based on Compound Flow Analysis (CFA) Methodolo
21、gy 99 6.7 Summary . 105 7. CALIBRATION TECHNIQUES . 106 7.1 Scale-Model Inlet Testing . 106 7.1.1 Inlet Performance Characterization 106 7.1.2 Model Test Program Planning 109 7.1.3 Testing and Data Reduction . 111 7.2 Scale-Model Nozzle Testing . 113 7.2.1 Nozzle Performance Characterization 113 7.2
22、.2 Model Test Program Planning 119 7.2.3 Test Procedure and Data Reduction . 124 7.3 Scale-Model Afterbody Testing . 126 7.3.1 Afterbody Performance Characterization 126 7.3.2 Model Test Program Planning 127 7.3.3 Testing and Data Reduction . 131 7.4 Engine Ground Testing . 132 7.4.1 Objectives and
23、General Requirements . 132 7.4.2 Ground-Level Test Facilities . 133 7.4.3 Altitude Test Facility 136 7.4.4 Other Ram Facilities 138 7.4.5 Special Considerations . 139 7.4.6 Engine Calibration Example 141 7.5 Turbo-powered Simulators 147 7.5.1 Types of Simulators 147 7.5.2 Operational Characteristics
24、 . 148 8. TEST DATA ACQUISITION SYSTEMS 150 8.1 In-Flight Measurements for Thrust Determination 150 8.1.1 Measurements Required for Gas-Path Methods . 151 8.1.2 Measurements Required for Nozzle Exit Traverse and Trunnion Methods 154 8.2 Data-Acquisition Instrumentation 155 8.2.1 Sensors . 155 8.3 Si
25、gnal Conditioning and Conversion . 160 8.4 Data Recording . 160 8.4.1 Cockpit Displays 160 8.4.2 Paper Trace 160 8.4.3 Special Instrumentation Package . 161 8.4.4 Ground Test Facility 161 8.5 Data Processing 161 8.5.1 Quick-Look 161 8.5.2 Sample Rate . 161 8.5.3 Synchronization . 162 8.6 Datum Check
26、s . 162 8.7 Calibration . 162 9. ANALYSIS AND VALIDATION OF THRUST DETERMINATION . 164 9.1 Pre-flight Engine Consistency Checks 164 9.1.1 Mass Flow Comparisons . 165 9.1.2 Thrust Checks . 167 9.2 In-Flight Engine Performance . 170 9.2.1 In-Flight Engine Tests . 170 9.2.2 Engine Environmental and Ins
27、tallation Effects . 172 9.2.3 Consistency of Installed Net Thrust and Engine Characteristics 174 9.2.4 In-Flight Engine Performance Summary . 175 9.3 Aerodynamic Characteristics 176 9.4 Examples of Test Analysis 176 9.4.1 Single-Exhaust Turbofan. 176 SAE INTERNATIONAL AIR1703A Page 4 of 316_ 9.4.2 I
28、ntermediate-Cowl Turbofan . 188 9.4.3 Mixed-Flow Afterburning Turbofan 190 10. NOTES 195 APPENDIX A COMMITTEE E-33 HISTORY . 196 APPENDIX B BIBLIOGRAPHY . 200 APPENDIX C THRUST AND DRAG ACCOUNTING 210 APPENDIX D BACKGROUND FOR THRUST/DRAG BOOKKEEPING . 244 APPENDIX E CASE STUDIES AND APPLICATIONS 26
29、0 FIGURE 1 AIRCRAFT IN-FLIGHT THRUST/DRAG DETERMINATION . 20 FIGURE 2 STATION NUMBERING SYSTEM 30 FIGURE 3 ISOLATED PROPULSION SYSTEM CONTROL VOLUMES 31 FIGURE 4 FORCES ON CONTROL VOLUME 37 FIGURE 5 DUAL-STREAM ENGINE CONTROL VOLUME 38 FIGURE 6 FORCES ACTING ON A PROPULSION SYSTEM 43 FIGURE 7 EXAMPL
30、E TEST MODELS . 45 FIGURE 8 TYPICAL THRUST/DRAG ACCOUNTING SYSTEM . 46 FIGURE 9 DRAG FORCE VARIATION WITH INLET MASS FLOW RATIO . 46 FIGURE 10 DRAG FORCE VARIATION WITH NOZZLE AREA AND NOZZLE PRESSURE RATIO 47 FIGURE 11 ISOLATED NACELLE INSTALLATION 58 FIGURE 12 LONG-DUCT TURBOFANS . 58 FIGURE 13 MI
31、XED-FLOW TURBOFAN 59 FIGURE 14 INTERMEDIATE OR SHORT-DUCT TURBOFAN . 59 FIGURE 15A F-22 . 60 FIGURE 15B F-15 . 60 FIGURE 15 TYPICAL INTEGRATED PROPULSION SYSTEM 60 FIGURE 16 TYPICAL EJECTOR NOZZLE, NON-AFTERBURNING 61 FIGURE 17 TYPICAL EJECTOR NOZZLE, AFTERBURNING . 62 FIGURE 18 TYPICAL 2-D INLET WI
32、TH RAMPS . 62 FIGURE 19 NOZZLE COEFFICIENT EXTRAPOLATION FOR LOW-BYPASS-RATIO ENGINE . 75 FIGURE 20 NOZZLE COEFFICIENT EXTRAPOLATION FOR HIGH-BYPASS-RATIO ENGINE 76 FIGURE 21A RERR CALCULATED VS. MEASURED TOTAL AIRFLOW COMPARISON . 78 FIGURE 21B RERR CALCULATED VS. MEASURED GROSS THRUST COMPARISON .
33、 79 FIGURE 21 RERR AIRFLOW AND THRUST COMPARISON PROCEDURES 79 FIGURE 22 RESIDUAL ERROR (RERR) 79 FIGURE 23 TRAVERSING RAKE ARRANGEMENT . 84 FIGURE 24A SIMPLIFIED 86 FIGURE 24B CONSIDERATIONS FOR THRUST VECTORING . 86 FIGURE 24 TRUNNION THRUST METHOD . 86 FIGURE 25 OVERALL PERFORMANCE METHOD FOR SIN
34、GLE-SPOOL FIXED-NOZZLE TURBOJET 88 FIGURE 26 COMPUTER-MODEL DATA MATCH APPROACH FOR SINGLE-SPOOL, FIXED-NOZZLE TURBOJET 89 FIGURE 27A GAS PATH/NOZZLE METHOD USING AREA-WEIGHTED NOZZLE PRESSURE RATIO 90 FIGURE 27B GROSS THRUST/FUEL FLOW CORRELATION METHOD 91 FIGURE 27C GROSS THRUST PARAMETER METHOD .
35、 92 FIGURE 27 IN-FLIGHT EVALUATION FOR SINGLE-EXHAUST TURBOFAN. 92 FIGURE 28A IN-FLIGHT AIRFLOW EVALUATION . 93 FIGURE 28B IN-FLIGHT THRUST EVALUATION . 94 FIGURE 28 GAS-PATH/NOZZLE METHOD FOR SEPARATE-STREAM TURBOFAN 94 FIGURE 29 GAS/PATH NOZZLE METHOD TW/F AND F/AP FOR MIXED-FLOW AFTERBURNING TURB
36、OFAN . 95 FIGURE 30A IFT METHOD 1 . 96 FIGURE 30B IFT METHOD 2, DRY 97 FIGURE 30C IFT METHOD 2, AFTERBURNER 97 FIGURE 30 CALCULATED PARAMETERS, CYCLE IMPLEMENTATION AND QUALITY CHECKS 97 FIGURE 31 NOMENCLATURE USED FOR COMPOUND FLOW ANALYSIS 100 FIGURE 32 CONTROL VOLUME USED TO SOLVE FOR CONDITIONS
37、AT THE MIXING DUCT EXIT 100 SAE INTERNATIONAL AIR1703A Page 5 of 316_ FIGURE 33 TOP-LEVEL CFA PROCESS FLOW MAP . 102 FIGURE 34 CFA IS USED TO DETERMINE IF THE NOZZLE IS CHOKED . 105 FIGURE 35 INLET CAPTURE RATIO DEFINITION 106 FIGURE 36A AIRFLOW CHARACTERISTICS . 107 FIGURE 36B INTERNAL PERFORMANCE
38、. 108 FIGURE 36C EXTERNAL PERFORMANCE 108 FIGURE 36 TYPICAL INLET PERFORMANCE CHARACTERISTICS 108 FIGURE 37A SEPARATE FLOW 114 FIGURE 37B LONG-DUCT MIXED FLOW . 114 FIGURE 37C VARIABLE-AREA CONVERGENT-DIVERGENT . 114 FIGURE 37 EXHAUST SYSTEM CONFIGURATIONS 114 FIGURE 38 TYPICAL SEPARATE-FLOW EXHAUST
39、 SYSTEM NOZZLE COEFFICIENT . 115 FIGURE 39 NOZZLE FLOW COEFFICIENT SUPPRESSION (ISOLATED NACELLE) . 116 FIGURE 40 ALTERNATE MIXED-FLOW EXHAUST SYSTEM PERFORMANCE PARAMETERS 118 FIGURE 41 CONVERGENT-DIVERGENT NOZZLE PERFORMANCE CURVES 119 FIGURE 42 NOZZLE-FLOW COEFFICIENT SUPPRESSION 120 FIGURE 43 EX
40、TRAPOLATION OF NOZZLE TEST DATA 122 FIGURE 44 MODEL GEOMETRIC SIMILARITIES 124 FIGURE 45 THROTTLE-DEPENDENT AFTERBODY FORCE INCREMENTS 126 FIGURE 46A WINGTIP SUPPORT 128 FIGURE 46B LOWER-FUSELAGE-MOUNTED STRUT 128 FIGURE 46C UPPER-FUSELAGE-MOUNTED STRUT . 128 FIGURE 46D REAR-ENTRY STING . 128 FIGURE
41、 46E COANNULAR REAR-ENTRY STING . 129 FIGURE 46 AFTERBODY MODEL SUPPORT SYSTEMS . 129 FIGURE 47 SUPPORT SYSTEM ISSUES . 129 FIGURE 48 OPEN-AIR TEST STAND . 134 FIGURE 49 GROUND-LEVEL TEST CELL . 135 FIGURE 50 ALTITUDE TEST CELL WITH OVERHEAD THRUST MEASURING SYSTEMS 136 FIGURE 51 ALLTITUDE TEST CELL
42、 WITH UNDER-ENGINE THRUST SLED . 137 FIGURE 52 GROUND-LEVEL TEST CELL WITH INLET RAM CAPABILITY . 139 FIGURE 53A GROSS THRUST/NOZZLE PRESSURE RATIO CORRELATION 143 FIGURE 53B GROSS THRUST/FUEL FLOW CORRELATION . 144 FIGURE 53C GROSS THRUST PARAMETER CORRELATION . 144 FIGURE 53 SINGLE-EXHAUST TURBOFA
43、N ATF CALIBRATION . 144 FIGURE 54 INTERMEDIATE-COWL TURBOFAN ATF CALIBRATION . 145 FIGURE 55 ATF CALIBRATION OF MIXED-FLOW AFTERBURNING TURBOFAN 146 FIGURE 56 SUBSONIC TURBO-POWERED SIMULATOR CROSS SECTION . 148 FIGURE 57 SUBSONIC TURBO-POWERED SIMULATOR 148 FIGURE 58 COMPACT MULTI-MISSION PROPULSIO
44、N SIMULATOR . 149 FIGURE 59 TYPICAL FLIGHT TEST MEASUREMENTS ON A TURBOFAN ENGINE 150 FIGURE 60 INSTRUMENTATION SYSTEM 150 FIGURE 61 EXAMPLES OF A REAL-TIME DATA SYSTEM 151 FIGURE 62 AIRFLOW DUCT CHECK (NON-AFTERBURNING TURBOJET ENGINE) . 166 FIGURE 63 TAILPIPE CONTINUITY CHECK METHOD (RAKE LOCATED
45、AT NOZZLE THROAT) . 166 FIGURE 64 SCALE MODEL CHECK THRUST COMPARISON - INITIAL RESULTS (NON-AFTERBURNING TURBOJET) 169 FIGURE 65 RESOLUTION OF SCALE MODEL AND FULL-SCALE ENGINE THRUST (NON-AFTERBURNING TURBOJET) 170 FIGURE 66 ENGINE PART-POWER CORRECTED THRUST VERSUS CORRECTED FUEL FLOW 171 FIGURE
46、68 ATF/FLIGHT-ENGINE THRUST VERSUS FUEL FLOW WITH COMPRESSOR BLEED AIRFLOW . 173 FIGURE 69 ENGINE CALIBRATION CHARACTERISTICS COMPARISON 174 FIGURE 70 FLIGHT AND ATF LOW- AND HIGH-PRESSURE ROTOR SPEED COMPARISON 179 FIGURE 71 2tH/N -DERIVED/FLIGHT DRAG CHARACTERISTICS. 181 FIGURE 72 FUEL-FLOW-DERIVE
47、D FLIGHT DRAG CHARACTERISTICS 182 FIGURE 73 COMPARISON OF ATF AND ENGINE-MOUNTED 6tP PRESSURE TRANSDUCER MEASUREMENTS 183 FIGURE 74 F/AP MODE 1-DERIVED FLIGHT DRAG CHARACTERISTICS 185 SAE INTERNATIONAL AIR1703A Page 6 of 316_ FIGURE 75 F/AP MODE 2-DERIVED FLIGHT DRAG CHARACTERISTICS 185 FIGURE 76 TW/F -DERIVED FLIGHT DRAG CHARACTERISTICS . 186 FIGURE 77 AIR VEHICLE SPECIFIC RANGE CORRELATION . 187 FIGURE 78 THRUST-STAND-MEASURED AND CALCULATED STATIC THRUST COMPARISON . 189 FIGURE 79 FLIGHT TEST COMPARISON OF INLET FLOW CALCULATIONS 189 FIGURE 80 FLIG
