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 theref
2、rom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2011 SAE International All rights reserved. No part of this publication ma
3、y 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: +1 724-776-4970 (outside US
4、A) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AIR5687AEROSPACEINFORMATIONREPORTAIR5687 Issued 2011-09Inlet / Engine Compatibility From Model
5、to Full Scale Development RATIONALEThe intent of this document is to capture the experience and lessons learned since approximately 1967 necessary to ensure that model-scale inlet total-pressure recovery and distortion data faithfully represent the corresponding full-scale inlet recovery and distort
6、ion characteristics. FOREWORDThe SAE S-16 Committee, Turbine Engine Inlet Flow Distortion, is pleased to dedicate this document to Mr. Gregg Turley. Gregg was a member of the Committee from 2001 until his untimely death in 2006. Gregg will be remembered for his quiet, understated approach and bringi
7、ng his knowledge, perceptions, and range of experiences to tasks at hand including this document. This document is a collection of lessons learned since the late 1960s by practitioners of this discipline including those of Gregg while working at Northrop Grumman Corporation. These will be a resource
8、 to both new and experienced inlet/engine compatibility practitioners for decades to come. This document has been cleared for public release per Case Number 88ABW-2010-2038. The SAE S-16 Committee welcomes input from both industry and government organizations relative to the contents of this documen
9、t. Please feel free to address any comments on this document to the Chairman, SAE S-16 Committee. TABLE OF CONTENTS 1. SCOPE 41.1 Purpose . 41.2 Application . 42. REFERENCES 42.1 Applicable Documents 42.1.1 SAE Publications . 42.2 Applicable References 42.3 Additional References . 62.4 Symbols and A
10、bbreviations 83. INTRODUCTION. 114. BACKGOUND. 124.1 Evolution of Inlet Development, Test, and Evaluation Practices Prior to the F-111 . 134.2 The F-111 Inlet/Engine Compatibility Experience . 165. CASE STUDIES 195.1 Case Studies Offering Correlations 195.1.1 RA-5C Case Study 195.1.2 YF-12 Case Stud
11、y . 245.1.3 F-15 Case Study . 28Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR5687 Page 2 of 945.1.4 B-1 Case Study . 355.1.5 F-18E/F Case Study 455.1.6 F-22 Case Study . 535.2 Case Studies
12、Offering Key Observations . 685.2.1 F-16 Case Study . 685.2.2 B-2 Case Study . 706. SIMILARITIES AND TEST TECHNIQUES . 736.1 Geometric Similarities . 736.1.1 Moldline and Scaling . 736.1.2 Subscale Model . 736.1.3 Full-Scale Wind Tunnel Hardware 756.2 Flow Similarities 766.3 CFD Simulation Technique
13、s . 776.4 Test and Evaluation Techniques. 786.4.1 Wind Tunnel Test Techniques 786.4.2 Flight Test Techniques 867. LESSONS LEARNED AND RECOMMENDATIONS 927.1 Lessons Learned 927.2 Recommendations 937.2.1 Recommendations For Research To Correct Discrepancies Noted In Lessons Learned . 937.2.2 Recommend
14、ations For Future Programs . 93LIST OF FIGURES FIGURE 1 INLET INSTALLATION OF THE BELL P-59 14FIGURE 2 P-59 INLET APERTURE AND DIVERTER . 14FIGURE 3 P-80 INLET INSTALLATION . 15FIGURE 4 F-89 INLET/DIVERTER INSTALLATION . 15FIGURE 5 F-100F INLET INSTALLATION . 15FIGURE 6 F-101 INLET CONFIGURATION WIT
15、H EXTERNAL DIVERTER AND SIDEPLATE . 16FIGURE 7 INLET SYSTEM FOR THE F-111 . 17FIGURE 8 RA-5C INLET SYSTEM 20FIGURE 9 RA-5C INLET WIND TUNNEL MODELS 21FIGURE 10 VARIATION OF TOTAL-PRESSURE RECOVERY WITH REYNOLDS ANDMACH NUMBERS, AND SCALE 22FIGURE 11 VARIATION OF DYNAMIC CIRCUMFERENTIAL DISTORTION WI
16、TH REYNOLDS NUMBER 23 FIGURE 12 YF-12 INLET AND INSTALLATION 24FIGURE 13 YF-12 INLET MODEL DETAILS . 25FIGURE 14 YF-12 INLET MODEL INSTRUMENTATION DETAILS . 26FIGURE 15 YF-12 PERFORMANCE AND DISTORTION, MACH 2.8 27FIGURE 16 YF-12 PERFORMANCE AND DISTORTION, MACH 2.1 27FIGURE 17 F-15 INLET CONFIGURAT
17、ION 28FIGURE 18 F-15 INLET TEST ARTICLES . 29FIGURE 19 EFFECT OF ENGINE PRESENCE ON PEAK DISTORTION 31FIGURE 20 EFFECT OF ENGINE PRESENCE ON INLET PERFORMANCE PARAMETERS . 32FIGURE 21 REPRESENTATIVE EFFECT OF REYNOLDS NUMBER AT MACH 0.6, D = 4 DEG, E = 0 DEG 33FIGURE 22 EFFECT OF FILTER FREQUENCY ON
18、 INLET DATA AT MACH 1.8, D = -2 DEG, E = 0 DEG 34FIGURE 23 B-1 AIRCRAFT AND INLET DETAILS 36FIGURE 24 0.1-SCALE B-1A IN AEDC TUNNEL 16S 37FIGURE 25 0.20-SCALE B-1A INSTALLED IN AEDC TUNNEL 16S 37FIGURE 26 FULL-SCALE B-1A IN AEDC TUNNEL 16T . 38FIGURE 27 DETAILS OF B-1A INLET WIND TUNNEL MODELS 39FIG
19、URE 28 EFFECT OF REYNOLDS NUMBER AND SCALE AT M = 0.85 41FIGURE 29 EFFECT OF REYNOLDS NUMBER AND SCALE AT M = 2.0 42FIGURE 30 COMPARISON OF FLIGHT TO WIND TUNNEL TEST . 43FIGURE 31 ENGINE EFFECTS AT M = 0 . 44FIGURE 32 ENGINE EFFECTS AT M = 2.2 44Copyright SAE International Provided by IHS under lic
20、ense with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR5687 Page 3 of 94FIGURE 33 F/A-18E INLET WIND TUNNEL MODEL 404 AND FLIGHT-TEST AIRCRAFT E2 . 45FIGURE 34 INLET RECOVERY AT TRANSONIC CRUISE CONDITIONS 47FIGURE 35 INLET RECOVERY VARIATION WITH UNIT
21、 REYNOLDS NUMBER . 48FIGURE 36 PEAK CIRCUMFERENTIAL DISTORTION DURING MANEUVERS AT TRANSONIC SPEEDS . 48FIGURE 37 PEAK RADIAL DISTORTION DURING MANEUVER AT TRANSONIC SPEEDS . 49FIGURE 38 PEAK TOTAL-PRESSURE PATTERNS DURING MANEUVER AT TRANSONIC SPEEDS 49FIGURE 39 PLANAR WAVE CONTENT AT TRANSONIC SPE
22、EDS 50FIGURE 40 INLET RECOVERY AT SUPERSONIC FLIGHT CONDITIONS 50FIGURE 41 PEAK CIRCUMFERENTIAL DISTORTION AT SUPERSONIC SPEEDS 51FIGURE 42 PEAK RADIAL DISTORTION AT SUPERSONIC SPEEDS . 51FIGURE 43 PLANAR WAVE CONTENT AT SUPERSONIC SPEEDS . 52FIGURE 44 PEAK TOTAL-PRESSURE PATTERNS AT SUPERSONIC SPEE
23、DS 52FIGURE 45 FULL-SCALE F-22 INLET WITH FIXED AND VARIABLE BLEED 54FIGURE 46 SUBSCALE F-22 INLET TESTED IN THE AEDC 16-FT TRANSONIC ANDSUPERSONIC WIND TUNNELS 54FIGURE 47 WIND TUNNEL INLET RAKE GEOMETRY . 56FIGURE 48 F119-PW-100 FLIGHT TEST ENGINE-FACE RAKE . 57FIGURE 49 FLIGHT TEST INLET RAKE GEO
24、METRY . 57FIGURE 50 REYNOLDS NUMBER CORRECTION 59FIGURE 51 STATISTICAL IMPACT OF SCREENING ONE SECOND VERSUS FIVE SECONDS OF DATATO DETERMINE WORST CASE DISTORTION INTENSITY 61FIGURE 52 WIND TUNNEL AND FLIGHT TEST CORRELATIONS AT 1-G TRIM FLIGHT, LOW ALTITUDES AND LOW-SUBSONIC FLIGHT CONDTIONS 63FIG
25、URE 53 WIND TUNNEL AND FLIGHT TEST CONDITIONS AT 1-G TRIM FLIGHT, MID-ALTITUDE AND HIGH-SUPERSONIC FLIGHT 65FIGURE 54 DISTORTION SUMMARY AT LOW-SUBSONIC SPEEDS WITH NEGATIVE AND POSITIVE AOA . 66FIGURE 55 DISTORTION SUMMARY, MID-TO HIGH-SUPERSONIC, NEGATIVE AND POSITIVE AOA . 66FIGURE 56 F-16 INLET
26、MODEL WITH SIMULATED PROBES 70FIGURE 57 F-16 INLET BUZZ TEST DATA 70FIGURE 58 EFFECT OF INLET BREAK ON CONSUMPTION OF FAN STABILITY PRESSURE RATIO. 72FIGURE 59 FULL-SCALE F-15 INLET WITH MODIFIED FOREBODY 75FIGURE 60 TYPICAL INLET WIND TUNNEL MODEL 79FIGURE 61 AIP RAKE IN MODEL . 80FIGURE 62 TYPICAL
27、 FLOW-PLUG ARRANGEMENT . 81FIGURE 63 TAPE TRANSITION DOTS . 83FIGURE 64 DISTORTION SCREENS FOR DIRECT-CONNECT ENGINE TESTING . 84FIGURE 65 INLET DISTORTION SCREEN INSTALLATION 84FIGURE 66 DISTORTION SCREEN SWIRL PATTERN . 85FIGURE 67 TYPICAL MILITARY FIGHTER AIRCRAFT INCREMENTAL ENVELOPE EXPANSIONVS
28、. A LIMITED SURVEY FOR WIND TUNNEL COMPARISON . 86FIGURE 68 TYPICAL LOW-SPEED ENVELOPE EXPANSION APPROACH SHOWING INTEGRATIONOF PROPULSION AND FLYING QUALITY MANUEVERS . 89FIGURE 69 EXAMPLE OF F-18 HARV FLIGHT TEST INSTRUMENTATION FOR INLET/ENGINECOMPATIBILITY TESTING 90LIST OF TABLES TABLE 1 EARLY
29、AIRCRAFT PROGRAMS OFFERING INSIGHT INTO THE EVOLUTION OFINLET/AIRFRAME INTEGRATION TECHNOLOGY 12TABLE 2 AIRCRAFT PROGRAMS OFFERING WIND TUNNEL TO FLIGHT CORRELATIONS OFINLET RECOVERY AND DYNAMIC TOTAL-PRESSURE DISTORTION . 13TABLE 3 F-15 TEST CONDITIONS . 30TABLE 4 TOLERANCES FOR TRIM AND MANEUVER F
30、LIGHT CONDITIONS . 88Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE AIR5687 Page 4 of 941. SCOPE This document reviews the state of the art for data scaling issues associated with air induction
31、system development for turbine-engine-powered aircraft. In particular, the document addresses issues with obtaining high quality aerodynamic data when testing inlets. These data are used in performance and inlet-engine compatibility analyses. Examples of such data are: inlet recovery, inlet turbulen
32、ce, and steady-state and dynamic total-pressure inlet distortion indices. Achieving full-scale inlet/engine compatibility requires a deep understanding of three areas: 1) geometric scaling fidelity (referred to here as just “scaling”), 2) impact of Reynolds number, and 3) ground and flight-test tech
33、niques (including relevant environment simulation, data acquisition, and data reduction practices). The Model-to-Full Scale Subcommittee of the S-16 Turbine Engine Inlet Flow Distortion Committee has examined archives and has obtained recollections of experts regarding air induction system developme
34、nt experience to produce this document. 1.1 Purpose The primary objective of this document is to provide a consolidated record of what is known regarding the effectiveness of wind-tunnel scale-model testing in the prediction of full-scale flight characteristics such as inlet recovery, inlet turbulen
35、ce,and steady-state and dynamic total-pressure inlet distortion. Discussion is offered regarding these findings in light of our current knowledge and understanding. Based on this discussion material, the SAE S-16 Committee has been able to achieve consensus on lessons learned and to provide recommen
36、dations. 1.2 Application This document focuses on turbine-engine-powered military air vehicles, including some recent advanced aircraft air-induction systems. No information is provided for commercial transport high-bypass turbofan installations, small turbo-jet/turbofan aircraft, turboprop aircraft
37、, turbine-engine-powered missiles, ground vehicle installations, or auxiliary power units. However, many of the lessons learned and recommendations made in this document are applicable to these installations as long as the user recognizes and understands the limitations of the information that he/sh
38、e is attempting to use. This statement is based on anecdotal discussions with engineers who work or have worked on such installations and who have judiciously and successfully applied these lessons and recommendations. 2. REFERENCES The following publications form a part of this document to the exte
39、nt specified herein. The latest issue of SAE publications will apply. The applicable issue of other publications will be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited here, the text of this document takes preced
40、ence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.2.1 Applicable Documents 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Can
41、ada) or 724-776-4970 (outside USA), www.sae.org.ARP1420 Gas Turbine Engine Inlet Flow Distortion Guidelines AIR1419 Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines AIR5866 An Assessment of Planar Waves AIR5686 A Methodology of Assessing Inlet Swirl Distortion 2.2 Applicable Re
42、ferences 2.2.1 Aerodynamics Research Branch, NACA Headquarters, “Bibliography of NACA and Other Reports on Air Inlets and Internal Flows,” NACA RM No. 8J05, October 1948. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without l
43、icense from IHS-,-,-SAE AIR5687 Page 5 of 942.2.2 Surber, L.E., and Robinson, C.P., “Survey of Inlet Development for Supersonic Aircraft,” AIAA 83-1164, June 1983.2.2.3 Smith, Robert, Jr., “Marrying Airframes and Engines in Ground Test Facilities An Evolutionary Revolution,” AIAA 95-0950, September
44、1995. 2.2.4 Davis, W.F. and Sherrer, R., “Aerodynamic Principles for the Design of Jet-Engine Induction Systems,” NACA RM A55F16.2.2.5 Alford, J.S., GER-1404, General Electric, “Inlet Flow Distortion Index,” International Days of Aeronautical Sciences, Paris, France, May 1957. 2.2.6 Schweikhard, W.G
45、., and Dennon, S.R., “Review and Evaluation of Recent Developments of Melick Inlet Dynamic Flow Distortion Prediction,” NASA CR 4061, May 1987, p. 78. 2.2.7 Air Force Aero Propulsion Laboratory, “Proceedings of the Air Force Airframe Propulsion Compatibility Symposium,” AFAPL TR-69-103, June, 1970.2
46、.2.8 Burcham, F.W., and Hughes, D., “Analysis of Inlet-Flight Pressure Fluctuations Leading To Engine Compressor Surge of an F-111A Airplane for Mach Numbers to 2.17,” AIAA Paper No. 70-624, June, 1970. 2.2.9 Behal, J.A., Belga, M.H., and Simons, D.E., “Wind Tunnel/Flight Data Correlation, Final Rep
47、ort Vol. I, II, III, and IV,” AFFDL TR-71-105, October 1971.2.2.10 Stevens, C.H., Spong, E.D., Nugent, J., and Neumann, H.C., “Reynolds Number, Scale, and Frequency Content Effects on F-15 Instantaneous Distortion,” AIAA 79-0104, January 1979. 2.2.11 Smeltzer, D.B., Smith, R.H., and Cubbison, R.W.,
48、“Wind Tunnel and Flight Performance of the YF-12 Inlet System,” AIAA 74-621, July 1974. 2.2.12 Stevens, C.H., Spong, E.D., and Hammock, M.S., “F-15 Inlet/Engine Test Techniques and Distortion Methodologies Studies, Vol. I, Technical Discussion,” NASA CR 144866, June 1976. 2.2.13 Farr, A.P., “Evaluation of F-15 Inlet Dynamic Distortion,” AIAA
