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| 040 | ⊔ | ⊔ | ‡aTRAAL ‡cTRAAL ‡dUtOrBLW |
| 049 | ⊔ | ⊔ | ‡aMAIN |
| 086 | 0 | ⊔ | ‡aD 217.22:67-39 |
| 100 | 1 | ⊔ | ‡aTetervin, Neal, ‡eauthor. |
| 245 | 1 | 3 | ‡aAn analytical investigation of the flat plate turbulent boundary layer in compressible flow / ‡cby Neal Tetervin. |
| 264 | ⊔ | 1 | ‡aWhite Oak, Maryland : ‡bUnited States Naval Ordnance Laboratory, ‡c1967. |
| 300 | ⊔ | ⊔ | ‡aix, 38 [88] pages : ‡billustrations ; ‡c28 cm. |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aNOLTR (Series) ; ‡v67-39 |
| 490 | 0 | ⊔ | ‡aAerodynamics research report no. 286 |
| 500 | ⊔ | ⊔ | ‡a"15 May 1967". |
| 504 | ⊔ | ⊔ | ‡aIncludes bibliographical references (pages 37-38) |
| 520 | ⊔ | ⊔ | ‡aThe concepts of eddy kinematic viscosity and eddy diffusivity are used to calculate skin friction and heat transfer coefficients for the turbulent boundary layer on a flat plate. The eddy kinematic viscosity, eddy diffusivity, and turbulent Prandtl number vary across the boundary layer. The Mach number range is from zero to ten. The surface to stream temperature ratio varies from one-half to eight, and includes the insulated surface. The friction results are compared with experimental data. Velocity and temperature profiles for the entire region from the surface to the outer edge are compared with experimental data. (Author). |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 650 | ⊔ | 0 | ‡aSkin friction (Aerodynamics) ‡0http://id.loc.gov/authorities/subjects/sh85123197 |
| 650 | ⊔ | 0 | ‡aTurbulent boundary layer. ‡0http://id.loc.gov/authorities/subjects/sh85138754 |
| 710 | 2 | ⊔ | ‡aNaval Ordnance Laboratory (White Oak, Md.) ‡0http://id.loc.gov/authorities/names/n79081705 ‡1http://id.loc.gov/rwo/agents/n79081705 |
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