دورية أكاديمية
Sting Interference Effects as Determined by Measurements of Dynamic Stability Derivatives, Surface Pressure, and Base Pressure for Mach Numbers 2 through 8
| العنوان: | Sting Interference Effects as Determined by Measurements of Dynamic Stability Derivatives, Surface Pressure, and Base Pressure for Mach Numbers 2 through 8 |
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| المؤلفون: | Uselton, Bob L, Cyran, Fred B |
| المساهمون: | ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN |
| المصدر: | DTIC AND NTIS |
| سنة النشر: | 1980 |
| المجموعة: | Defense Technical Information Center: DTIC Technical Reports database |
| مصطلحات موضوعية: | Test Facilities, Equipment and Methods, Guided Missile Dynam, Config & Cntrl Surfaces, BLUNT BODIES, HYPERSONIC VELOCITY, SUPERSONIC FLOW, WIND TUNNEL TESTS, ANGLE OF ATTACK, BASE PRESSURE, DAMPING, DYNAMIC TESTS, INTERFERENCE, LAMINAR BOUNDARY LAYER, MACH NUMBER, MEASUREMENT, NOSE CONES, OSCILLATION, PITCH(MOTION), STATIC STABILITY, STING MOUNTS, TURBULENT BOUNDARY LAYER, WIND TUNNEL MODELS, LPN-ARO-V41A/B-W4A, LPN-ARO-V32F-09, LPN-ARO-V32A-A1A, LPN-ARO-41A/B-N9A, LPN-ARO-V32A-R0A, PE65807F |
| الوصف: | Wind tunnel tests were conducted to provide support interference information for planning and directing wind tunnel tests at supersonic and hypersonic Mach numbers. Sting-length and sting-diameter effects on base and surface pressures of a blunt 6-deg cone with a sliced base were investigated at Mach numbers 2, 3, 5, and 8. Dynamic stability tests on a blunt 7-deg cone were also conducted at Mach numbers 2, 5, and 8. The objectives of the 7-deg cone tests were to define critical sting lengths as determined by the measurement of dynamic stability derivatives, static pitching moment, and base pressure. Two frequencies of oscillation were investigated, and data were obtained for laminar, transitional, and turbulent boundary-layer conditions at the model base. The data from the 6- and 7-deg cone tests showed that the critical sting length depended on the interference indicator, Mach number, angle of attack, state of the model boundary layer, and frequency of oscillation. The critical sting length was generally less for models with turbulent boundary layers than for those with laminar boundary layers. A critical sting length of 2.5 model diameters was determined to be suitable for all test conditions that produced a turbulent boundary layer at or ahead of the model base. ; Prepared in cooperation with ARO, Inc., Tullahoma, TN. |
| نوع الوثيقة: | text |
| وصف الملف: | text/html |
| اللغة: | English |
| العلاقة: | http://www.dtic.mil/docs/citations/ADA091115Test |
| الإتاحة: | http://www.dtic.mil/docs/citations/ADA091115Test http://oai.dtic.mil/oai/oai?&verb=getRecord&metadataPrefix=html&identifier=ADA091115Test |
| حقوق: | Approved for public release; distribution is unlimited. |
| رقم الانضمام: | edsbas.35B219BE |
| قاعدة البيانات: | BASE |
| الوصف غير متاح. |