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Turbulence Effects on the High Angle of Attack Aerodynamics of a Vertically Launched Missile

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Turbulence Effects on the High Angle of Attack Aerodynamics of a Vertically Launched Missile Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 1988 Turbulence effects on the high angle of attack aerodynamics of a vertically launched missile. Rabang, M. Peter. http://hdl.handle.net/10945/23433 NAVAL POSTGRADUATE SCHOOL Monterey , California THESIS -PKKZ." TURBULENCE EFFECTS ON THE HIGH ANGLE OF ATTACK AERODYNAMICS OF A VERTICALLY LAUNCHED MISSILE bv M. Peter Rabang t m • June 1988 Thesis Advisor Richard M. Howard Approved for public release; distribution is unlimited. 12k 2275 nclassified RKPORT DOCl MEN 1 A I ION PAGE b Restrictive Marki a Rerori Secu:it\ C : Unclassified .- nr 3 D;<:nbution Availability of Report Approved for public release: distribution is unlimited : Dow ngi adins Sc ~ _ rr na Organ zai Ret " SumbeT s 5 Monitorins Orcanizanon Report Numbensl a Name of Performing 0:;ar.:zation 6b Office Svmbol "a Name of Monitoring Organization \'aval Postaraduate School if applicable 33 Naval Postgraduate School c Address (city state s-.J ZIP code "b Address (city, state, and ZIP code) vlonterev. CA 93943-5000 Monterev. CA 93943-5000 Name of Funding Sponsoring Organization Sb Office Symbol Procurement Instrument Identification Number i if applicable state, and ZIP code) 10 Source of Fund'.na Numbers Program Element No Project No Task No Work L nit Accessii n No TURBULENCE EFFECTS ON THE HIGH ANGLE OF ATTACK AERODYNAMICS JV A VERTICALLY LAUNCHED MISSILE I P.-—;. \uthc M. Peter Rahans Report I3b I lme Co\e- 14 Date of Report (vear, month, day 15 Pase Count - i - To I n-'s Thesis June 1988 165 policy ; \otauon The views expressed in this thesis are those of the author and do not reflect the official or po- sit icnoftheDepjuTrnent^^ r c 1 8 Subject Term; a£ on reverse if necessary and identify by block number) Vortex. Vertical Launch. Surface to Air Missile, High Angle of Attack Aerodynamics, Fie : Turbulence. Bodv of Revolution iry r. block numbi A subsonic wind tunnel investigation was conducted at the Naval Postgraduate School Wind Tunnel Test Facility to ex- amine the effects ot grid generated turbulence on the high angle of attack aerodynamics of a vertically launched missile. Four turbulence generating grids produced turbulence with length scale to missile model diameter ratios of 1.05, 0.89, 0.62. and 0.15 with respective turbulence intensities of 3.31%. 2.78%. 1.88%, and 0.47%. The test model is representative of current cruciform wing missiles with low aspect ratio wings and long root chords. The tangent ogive nose has a nose fineness ratio of 2.29. Three separate body configurations were tested with and without the turbulence generating grids. One configuration s was a body in isolation and the other two were wing and tail configurations at and 45" roll angles. All test runs were s : : -5 . scales ap- conducted at Red 3: 1. 1x10 over an angle of attack range of to 95 Results indicate that as turbulence length proach body diameter size, the angle of attack for the onset of asymmetric vortices was delayed and the side force magnitude was reduced. The vortices generated by the nose of the missile continue to dominate the afterbody vortices for body config- urations with and without wines regardless of the turbulence conditions. H Distribution Availability of Abstract 21 Abstract Security Classification B unclassified unlimited D same as recort D DT1C users L'nclassified 12a Name of Responsible Individual 22b Telephone i include Area code) 22c Office Svmbol Richard M. Howard (4)8, 646-2870 67Ho )D FORM 1473A4 MAR 83 APR edition may be used until exhausted security classification of this page All other editions are obsolete Unclassified Approved for public release; distribution is unlimited. Turbulence Effects on the High Angle of Attack Aerodynamics of a Vertically Launched Missile by M. Peter Rabang Lieutenant, United States Navy B.S., University of South Carolina, 1981 Submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE IN ENGINEERING SCIENCE from the NAVAL POSTGRADUATE SCHOOL June 198S ABSTRACT A subsonic wind tunnel investigation was conducted at the Naval Postgraduate School Wind Tunnel Test Facility to examine the effects of grid generated turbulence on the high angle of attack aerodynamics of a vertically launched missile. Four turbu- lence generating grids produced turbulence with length scale to missile model diameter ratios of 1.05, 0.89. 0.62, and 0.15 with respective turbulence intensities of 3.31%, 2.78%. 1.88%, and 0.47%. The test model is representative of current cruciform wing missiles with low aspect ratio wings and long root chords. The tangent ogive nose has a nose fineness ratio of 2.29. Three separate body configurations were tested with and without the turbulence generating grids. One configuration was a body in isolation and the other two were wing and tail configurations at 0° and 45° roll angles. All test runs were conducted at Re„«l. 1x10s over an angle of attack range of -5° to 95°. Results in- dicate that as turbulence length scales approach body diameter size, the angle of attack for the onset of asymmetric vortices was delayed and the side force magnitude was re- duced. The vortices generated by the nose of the missile continue to dominate the afterbody vortices for body configurations with and without wings regardless of the turbulence conditions. in THESIS DISCLAIMER The reader is cautioned that computer programs developed in this research may not have been exercised for all cases of interest. While even7 effort has been made, within the time available, to ensure that the programs are free of computational and logic errors, they cannot be considered validated. Any application of these programs without addi- tional verification is at the risk of the user. IV TABLE OF CONTENTS I. INTRODUCTION 1 A. BACKGROUND 1 B. HIGH ANGLE OF ATTACK AERODYNAMICS 2 1. Vortex Regions 2 a. Regime I - [0° < a < a sv ] 4 b. Regime II - [a sv < a < a AV] 4 c. Regime III - [a AV < a < a LT ] 4 d. Regime IV - [a^ < a < 90°] 4 2. Two Dimensional Crossflow 5 3. Three Dimensional Vortices 8 C. LIFTING SURFACE EFFECTS 10 1. Wings 10 2. Strakes 11 3. Tails 12 D. TURBULENCE 12 1. Intensity and Length Scale 12 2. Boundary Layer Effects 14 3. Vortex effects 15 E. VSLAM LAUNCH ENVIRONMENT 15 1. The Marine Environment 15 2. Turbulence 16 3. Crosswind 17 4. Ship Ainvake 17 5. Additional launch considerations 18 II. EXPERIMENT AND PROCEDURES 19 A. APPARATUS 19 1. Wind Tunnel 19 2. VSLAM Model 21 3. Balance 23 4. Model Balance Support 23 5. Turbulence Grids 25 6. Data Acquisition Hardware 29 7. Data Acquisition Software 31 B. EXPERIMENTAL CONDITIONS 31 C. EXPERIMENTAL PROCEDURE 33 1. Balance Calibration 33 2. Prerun Calibration and Test 33 3. Data Collection 34 4. Preliminary Runs 34 D. EXPERIMENTAL CORRECTIONS 35 III. RESULTS 37 A. VARIATIONS IN NOSE ROLL ANGLE 37 B. DATA REPEATABILITY 39 C. BODY IN ISOLATION 40 D. WINGS AND STRAKES WITHOUT TURBULENCE 44 E. WINGS AND STRAKES WITH TURBULENCE 51 F. NORMAL FORCE RESULTS 52 G. SIDE FORCE TO NORMAL FORCE RATIO 52 IV. CONCLUSIONS AND RECOMMENDATIONS 69 APPENDIX A. BALANCE CALIBRATION CONSTANTS 71 APPENDIX B. RUN MATRIX 73 APPENDIX C. NUMERICAL DATA LISTING 76 APPENDIX D. DATA ACQUISITION PROGRAM 129 APPENDIX E. COEFFICIENTS TRANSLATION PROGRAM 139 LIST OF REFERENCES 144 VI INITIAL DISTRIBUTION LIST 149 Vll LIST OF TABLES Table 1. BALANCE CHANNELS 23 Table 2. GRID SPECIFICATIONS 26 Table 3. GRID TURBULENCE PARAMETERS 27 Table 4. VLSAM MODEL BLOCKAGE 36 Vlll 1 LIST OF FIGURES Figure 1. Vortex Generation Regimes 3 Figure 2_ Two dimensional crossflow about a cylinder 5 Figure 3. Side force to normal force ratio 6 Figure 4. Flow over a delta wing 11 Figure 5. Naval Postgraduate School Low Speed Wind Tunnel 20 Figure 6. Drawing of VLSAM model 22 Figure 7. Photograph of VLSAM model in the test section 24 Figure S. Planview of VLSAM model in the test section 25 Figure 9. Grid Turbulence Intensity 26 Figure 10. Grid Turbulence Length Scales 27 Figure 11. Turbulence Grids 2. 3, and 4 28 Figure 1 Turbulence Grid 1 installed in the wind tunnel 29 Figure Data Acquisition Hardware 30 Figure 14. Body configurations and reference system 32 Figure 15. Blockage factors 36 Figure 16. Side force variations with nose roll angle 38 Figure 17. Side force variations with nose roll angle 38 Figure 18. Data Repeatability Runs 39 Figure 19. R0B802 40 Figure 20. R1B801 42 Figure 21. R2B80I 42 Figure ->") R3BS01 43 Figure 23. R4B801 43 Figure 24. R0AS03 45 Figure 25. ROC802 45 Figure 26. R1A804 46 Figure 27. R2AS01 46 Figure 28. R3A801 47 Figure 29. R4A801 47 Figure 30. R1C802 48 Fieure 31. R2C801 48 IX Figure 32. R3C801 49 Figure 33. R4C801 49 Figure 34. R0B802 ' 53 Figure 35. R1BS01 54 Figure 36. R2B801 54 Figure 37. R3B801 55 Figure 38. R4B801 55 Figure 39. ROA803 56 Figure 40. ROC802 56 Figure 41. R1A804 57 Figure 42. R2A801 57 Figure 43. R3AS01 58 Figure 44. R4A801 58 Figure 45. R1CS02 59 Figure 46. R2C801 59 Figure 47. R3C801 60 Figure 48. R4C801 60 Figure 49. R0B802 61 Figure 50. R1B801 61 Figure 51. R2BS01 62 Figure 52. R3B801 62 Figure 53. R4B801 63 Figure 54. ROA803 63 Figure 55. R1AS04 64 Figure 56. R2A801 64 Figure 57. R3AS01 65 Figure 58. R4AS01 65 Figure 59. ROC802 66 Figure 60. R1C802 66 Figure 61. R2C801 67 Figure 62. R3C801 67 Figure 63. R4C801 68 Figure 64. Balance Calibration Constants 71 Figure 65. Balance Calibration Constants 72 — NOMENCLATURE A axial force A d base area AOA angle of attack —^~— c n normal force coefficient.
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