Further experiments on impact-pressure probes in a low-density, hypervelocity flow

LDR 03016nam a2200409Ii 4500
001 102893740
003 MiAaHDL
005 20241209000000.0
006 m d
007 cr bn ---auaua
008 220711s1962 tnua bt f000 0 eng d
035 ⊔ ⊔ ‡a(MiU)99187625258606381
035 ⊔ ⊔ ‡asdr-miu.99187625258606381
035 ⊔ ⊔ ‡a(OCoLC)1335037963
035 ⊔ ⊔ ‡a(GWLA)gwla on1335037963
040 ⊔ ⊔ ‡aTRAAL ‡beng ‡erda ‡cTRAAL
049 ⊔ ⊔ ‡aMAIN
086 0 ⊔ ‡aD 301.45/33-2:62-208
100 1 ⊔ ‡aBailey, A. B., ‡eauthor.
245 1 0 ‡aFurther experiments on impact-pressure probes in a low-density, hypervelocity flow / ‡cA.B. Bailey.
264 ⊔ 1 ‡aArnold Air Force Station, Tennessee : ‡bArnold Engineering Development Center, Air Force Systems Command, United States Air Force, ‡c1962.
300 ⊔ ⊔ ‡a29 pages : ‡billustrations, ‡c28 cm
336 ⊔ ⊔ ‡atext ‡btxt ‡2rdacontent
337 ⊔ ⊔ ‡aunmediated ‡bn ‡2rdamedia
338 ⊔ ⊔ ‡avolume ‡bnc ‡2rdacarrier
490 0 ⊔ ‡aAEDC-TDR ; ‡v62-208
500 ⊔ ⊔ ‡aReport prepared by ARO, Inc., a subsidiary of Sverdrup and Parcel, Inc.
500 ⊔ ⊔ ‡a"November 1962."
504 ⊔ ⊔ ‡aIncludes bibliograqphic references (page 7-8).
520 ⊔ ⊔ ‡aAn investigation of the behavior of flat-faced, impact-pressure probes with a range of orificeto-probe diameter ratios was made in heated A under conditions where free stream Mach. = 4 to 14, gas temperature = 2700 to 4300 K, and Reynolds number (based on outside probe diameter and conditions behind a normal shock)/in. = 30 to 430. At the lower Reynolds numbers the measured impact pressure was found to decrease with the pressure sensing orifice size. This result agrees with that found in heated N. As the Reynolds number increased this orifice effect became less significant, and at the higher Reynolds numbers no decrease in measured impact pressure was noted for the smallest orifice tested. This tends to confirm the assumption made in some experiments on impact-pressure probes in a low-density hypervelocity flow (AD-268 391) that this behavior is caused by a thermomolecular flow effect. Because this effect is a function solely of pressure at a particular temperature, the greater the pressure the smaller the effect. When Re2 times the square root of density in free stream over density in normal shock is less than 800 in A the measured impact pressure was less than the true impact pressure and decreased to a minimum value, approximately 93% of the true value. As the Reynolds number decreased still further, the viscous effects became dominant, and there was a sharp increase in the measured impact pressure. (Author).s
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 0 ‡aAerodynamics, Hypersonic.
650 ⊔ 0 ‡aAerodynamic load.
650 ⊔ 0 ‡aPressure gages ‡xCalibration.
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)
899 ⊔ ⊔ ‡a39015104951317
CID ⊔ ⊔ ‡a102893740
DAT 0 ⊔ ‡a20220802101951.0 ‡b20241209000000.0
DAT 1 ⊔ ‡a20241209061151.0 ‡b2024-12-09T14:47:12Z
DAT 2 ⊔ ‡a2024-07-29T17:30:02Z
CAT ⊔ ⊔ ‡aSDR-MIU ‡cmiu ‡dALMA ‡lprepare.pl-004-008
FMT ⊔ ⊔ ‡aBK
HOL ⊔ ⊔ ‡0sdr-miu.99187625258606381 ‡aMiU ‡bSDR ‡cGWLA ‡pmdp.39015104951317 ‡sMIU ‡199187625258606381
974 ⊔ ⊔ ‡bMIU ‡cGWLA ‡d20241209 ‡sgoogle ‡umdp.39015104951317 ‡y1962 ‡rpd ‡qbib ‡tUS fed doc