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| 008 | 220524s1977 tnua bt f000 0 eng d | ||
| 035 | ⊔ | ⊔ | ‡a(MiU)99187625453606381 |
| 035 | ⊔ | ⊔ | ‡asdr-miu.99187625453606381 |
| 035 | ⊔ | ⊔ | ‡a(OCoLC)1319732212 |
| 035 | ⊔ | ⊔ | ‡a(GWLA)gwla on1319732212 |
| 040 | ⊔ | ⊔ | ‡aTRAAL ‡beng ‡erda ‡cTRAAL |
| 049 | ⊔ | ⊔ | ‡aMAIN |
| 086 | 0 | ⊔ | ‡aD 301.45/33: 76-161 |
| 100 | 1 | ⊔ | ‡aSpratley, A. V., ‡eauthor. |
| 245 | 1 | 3 | ‡aAn investigaion of boattail geometry and Reynolds number effects on forebody and afterbody drag at transonic Mach numbers / ‡cA.V. Spratley. |
| 264 | ⊔ | 1 | ‡aArnold Air Force Base, Tennessee : ‡bArnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, ‡c1977. |
| 300 | ⊔ | ⊔ | ‡a128 pages : ‡billustrations ; ‡c28 cm |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aAEDC-TR ; ‡v76-161 |
| 500 | ⊔ | ⊔ | ‡a"February 1977." |
| 500 | ⊔ | ⊔ | ‡a"Final Report: 28 -- 31 January 1976." |
| 504 | ⊔ | ⊔ | ‡aIncludes bibliographical references (pages 17-18). |
| 520 | ⊔ | ⊔ | ‡aAn experimental investigation was conducted in the AEDC 16-foot Transonic Wind Tunnel (16T) to determine both Reynolds number and nozzle afterbody configuration effects on model forebody and afterbody drag. The model was a sting-mounted body of revolution with interchangeable contoured, cylindrical, and 15-deg boattail configurations. Pressure and force data were obtained at Mach numbers from 0.60 to 1.40 and at unit Reynolds numbers from 1,470,000 per foot to 5,300,000 per foot. The experimental results showed that large variations in afterbody drag levels produced no significant change in forebody drag. The data also revealed that all three configurations exhibited little or no Reynolds number dependence subsonically and that only the 15-deg boattail afterbody was affected by Reynolds number supersonically. It was also demonstrated that data precision and wind tunnel calibration can have a significant effect on model drag and should be given careful consideration. (Author). |
| 536 | ⊔ | ⊔ | ‡aReport supported by the Air Force Systems Command and prepared by ARO, Inc, under Program Element, ‡e65807F. |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 650 | ⊔ | 0 | ‡aAerodynamics, Transonic. |
| 650 | ⊔ | 0 | ‡aJet nozzles. |
| 650 | ⊔ | 0 | ‡aDrag (Aerodynamics) |
| 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 | ⊔ | ⊔ | ‡a39015104975571 |
| CID | ⊔ | ⊔ | ‡a102893278 |
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