Measurements of a supersonic favorable-pressure-gradient turbulent boundary layer with heat Transfer : part 1 -data compilation

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086 0 ⊔ ‡aD 217.22:73-224
100 1 ⊔ ‡aVoisinet, Robert L. P., ‡eauthor.
245 1 0 ‡aMeasurements of a supersonic favorable-pressure-gradient turbulent boundary layer with heat Transfer : ‡bpart 1 -data compilation. / ‡cRobert L. P. Voisinet and Roland E. Lee.
264 ⊔ 1 ‡aSilver Spring, Maryland : ‡bNaval Ordnance Laboratory, ‡c1973.
300 ⊔ ⊔ ‡a124 pages (various pagings) : ‡billustrations ; ‡c28 cm
336 ⊔ ⊔ ‡atext ‡btxt ‡2rdacontent
337 ⊔ ⊔ ‡aunmediated ‡bn ‡2rdamedia
338 ⊔ ⊔ ‡avolume ‡bnc ‡2rdacarrier
490 0 ⊔ ‡aNOLTR (Series) ; ‡v73-224
500 ⊔ ⊔ ‡a12 December 1973.
500 ⊔ ⊔ ‡aAIRTASK A32 320/292/69/R009-02-030.
504 ⊔ ⊔ ‡aIncludes bibliographic references.
506 ⊔ ⊔ ‡aAPPROVED FOR PUBLIC RELEASE.
520 3 ⊔ ‡aThe results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 0 ‡aFluid mechanics.
650 ⊔ 0 ‡aWind tunnels.
650 ⊔ 0 ‡aNozzles.
650 ⊔ 0 ‡aHeat ‡xTransmission.
650 ⊔ 0 ‡aSkin friction (Aerodynamics)
650 ⊔ 0 ‡aTurbulent boundary layer.
700 1 ⊔ ‡aLee, Roland E., ‡eauthor.
710 2 ⊔ ‡aNaval Ordnance Laboratory (White Oak, Md.)
730 0 ⊔ ‡aTechnical Report Archive & Image Library (TRAIL)
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