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| 001 | 102893286 | ||
| 003 | MiAaHDL | ||
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| 006 | m d | ||
| 007 | cr bn ---auaua | ||
| 008 | 220524s1976 tnua rbt f000 0 eng d | ||
| 035 | ⊔ | ⊔ | ‡a(MiU)99187625480706381 |
| 035 | ⊔ | ⊔ | ‡asdr-miu.99187625480706381 |
| 035 | ⊔ | ⊔ | ‡a(OCoLC)1319732236 |
| 035 | ⊔ | ⊔ | ‡a(GWLA)gwla on1319732236 |
| 040 | ⊔ | ⊔ | ‡aTRAAL ‡beng ‡erda ‡cTRAAL |
| 049 | ⊔ | ⊔ | ‡aMAIN |
| 086 | 0 | ⊔ | ‡aD 301.45/33: 76-112 |
| 100 | 1 | ⊔ | ‡aHsieh, T., ‡eauthor. |
| 245 | 1 | 3 | ‡aAn investigation of separated flow about a hemisphere-cylinder at 0- to 19-deg incidence in the Mach number range from 0.6 to 1.5 / ‡cWilliam Lee Peters. |
| 264 | ⊔ | 1 | ‡aArnold Air Force Base, Tennessee : ‡bArnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, ‡c1976. |
| 300 | ⊔ | ⊔ | ‡a118 pages : ‡billustrations ; ‡c28 cm |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aAEDC-TR ; ‡v76-112 |
| 500 | ⊔ | ⊔ | ‡a"November 1976." |
| 500 | ⊔ | ⊔ | ‡a"Final Report: October 1974 -- June 1976." |
| 504 | ⊔ | ⊔ | ‡aIncludes bibliographical references (pages 28- 30). |
| 520 | ⊔ | ⊔ | ‡aThe objective of this investigation was to evaluate various jet simulation parameters in an attempt to establish a method of matching hot jet interference with cold jet flows. Successful parameters were determined based on their ability to correlate integrated afterbody pressure drag, a measurement of aerodynamic interference, for jet flows of varying total temperature. Data used in this investigation were obtained from experiments conducted in the AEDC Propulsion Wind Tunnel (16T) with three different isolated nozzle/afterbody configurations at free-stream Mach numbers from 0.6 to 1.5. Gas temperature effects on pressure drag were acquired with a convergent nozzle utilizing an air/ethylene burner to produce gas temperatures from 540 to 3,300 R. In addition, the jet effects of varying internal nozzle geometry, specifically nozzle divergence half-angle and nozzle exit-to-throat area ratio, were investigated utilizing high-pressure air as the nozzle exhaust gas. Jet simulation parameters were evaluated for jet flows where nozzle exit-to-throat area ratio was varied from 1.0 to approximately 1.5 and where divergence half-angle was varied from 0 to 10 deg. |
| 533 | ⊔ | ⊔ | ‡aPhotocopy. |
| 536 | ⊔ | ⊔ | ‡aReport supported by the Air Force Systems Command and prepared by ARO, Inc, under Program Element, ‡e62201F. |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 650 | ⊔ | 0 | ‡aAerodynamics, Transonic. |
| 650 | ⊔ | 0 | ‡aCylinders ‡xAerodynamics. |
| 710 | 1 | ⊔ | ‡aUnited States. ‡bAir Force. ‡bSystems Command, ‡eissuing body. |
| 710 | 2 | ⊔ | ‡aArnold Engineering Development Center, ‡esponsor. |
| 710 | 2 | ⊔ | ‡aARO, Inc., ‡esponsor. |
| 730 | 0 | ⊔ | ‡aTechnical Report Archive & Image Library (TRAIL) |
| 899 | ⊔ | ⊔ | ‡a39015104975530 |
| CID | ⊔ | ⊔ | ‡a102893286 |
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| DAT | 2 | ⊔ | ‡a2024-07-23T17:30:02Z |
| CAT | ⊔ | ⊔ | ‡aSDR-MIU ‡cmiu ‡dALMA ‡lprepare.pl-004-008 |
| FMT | ⊔ | ⊔ | ‡aBK |
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