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| 007 | cr bn ---auaua | ||
| 008 | 030917s1973 tnua bt f000 0 eng d | ||
| 035 | ⊔ | ⊔ | ‡a(MiU)99187625445906381 |
| 035 | ⊔ | ⊔ | ‡asdr-miu.99187625445906381 |
| 035 | ⊔ | ⊔ | ‡a(OCoLC)53036212 |
| 035 | ⊔ | ⊔ | ‡a(GWLA)gwla ocm53036212 |
| 040 | ⊔ | ⊔ | ‡aCIN ‡beng ‡erda ‡cCIN ‡dOCLCQ ‡dOCLCF ‡dOCLCO ‡dOCLCQ ‡dOCLCO ‡dTRAAL |
| 049 | ⊔ | ⊔ | ‡aMAIN |
| 050 | ⊔ | 4 | ‡aTL571 ‡b.C63 1973 |
| 086 | 0 | ⊔ | ‡aD 301.45/33:73-36 |
| 100 | 1 | ⊔ | ‡aCoats, Jack D., ‡eauthor. |
| 245 | 1 | 0 | ‡aInvestigation of the effects of nose bluntness on natural and induced boundary-layer transition on axisymmetric bodies in supersonic flow / ‡cJack D. Coats. |
| 264 | ⊔ | 1 | ‡aArnold Air Force Base, Tennessee : ‡bVon Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, ‡c1973. |
| 300 | ⊔ | ⊔ | ‡aviii, 52 pages : ‡billustrations ; ‡c27 cm. |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aAEDC-TR-73-36 |
| 500 | ⊔ | ⊔ | ‡aReport was prepared by ARO, Inc., a subsidiary of Sverdrup & Parcel and Associates, Inc. |
| 500 | ⊔ | ⊔ | ‡aAbstract. |
| 500 | ⊔ | ⊔ | ‡a"February 1973"--Cover. |
| 504 | ⊔ | ⊔ | ‡aIncludes bibliographical references (pages 49-53). |
| 520 | ⊔ | ⊔ | ‡aA series of tests has been conducted at free-stream Mach numbers four and eight to determine the effectiveness of three-dimensional boundary-layer trips in promoting transition on very blunt axisymmetric bodies with near equilibrium wall temperatures. Temperature distributions obtained with temperature sensing gages inserted in the model surface were used to locate boundary-layer transition at Mach number four, and qualitative results, based on pitot pressure measurements, were obtained at Mach number eight. A simple modification of a technique proposed by van Driest and Blummer for determining an effective trip size for blunt bodies is shown to yield a correlation applicable to their data on a sphere at Mach number two and the present configurations at Mach number four. |
| 536 | ⊔ | ⊔ | ‡aARO, Inc. ‡e65402234 ‡fVT0747 |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 650 | ⊔ | 7 | ‡aBoundary layer. ‡2fast ‡0(OCoLC)fst00837095 |
| 650 | ⊔ | 7 | ‡aAxial flow. ‡2fast ‡0(OCoLC)fst00824470 |
| 650 | ⊔ | 7 | ‡aAirplanes ‡xModels ‡xAerodynamics. ‡2fast ‡0(OCoLC)fst00803300 |
| 650 | ⊔ | 7 | ‡aAerodynamics, Supersonic. ‡2fast ‡0(OCoLC)fst00798221 |
| 650 | ⊔ | 6 | ‡aÉcoulement axial. ‡0(CaQQLa)201-0419079 |
| 650 | ⊔ | 6 | ‡aCouche limite. ‡0(CaQQLa)201-0009010 |
| 650 | ⊔ | 6 | ‡aAérodynamique supersonique. ‡0(CaQQLa)201-0000388 |
| 650 | ⊔ | 0 | ‡aAirplanes ‡xModels ‡xAerodynamics. |
| 650 | ⊔ | 0 | ‡aAxial flow. |
| 650 | ⊔ | 0 | ‡aBoundary layer. |
| 650 | ⊔ | 0 | ‡aAerodynamics, Supersonic. |
| 650 | ⊔ | 0 | ‡aSpace vehicles ‡xAtmospheric entry. |
| 710 | 2 | ⊔ | ‡aARO, Inc., ‡esponsor. |
| 710 | 2 | ⊔ | ‡aArnold Engineering Development Center, ‡esponsor. |
| 710 | 1 | ⊔ | ‡aUnited States. ‡bAir Force. ‡bSystems Command, ‡eissuing body. |
| 730 | 0 | ⊔ | ‡aTechnical Report Archive & Image Library (TRAIL) |
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| DAT | 1 | ⊔ | ‡a20230928062550.0 ‡b2024-07-29T17:35:42Z |
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| 974 | ⊔ | ⊔ | ‡bMIU ‡cGWLA ‡d20240729 ‡sgoogle ‡umdp.39015104952653 ‡y1973 ‡rpd ‡qbib ‡tUS fed doc |