Accession Number:

AD0263571

Title:

SEQUENTIAL ANALYSIS WITH APPLICATIONS TO RADAR DETECTION

Descriptive Note:

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE ELECTRONIC SYSTEMS LAB

Personal Author(s):

Report Date:

1961-08-01

Pagination or Media Count:

1.0

Abstract:

AD-263 5719 5 AD-263 572Div. 9U TIPSENT OT price .75 Natio l ero au ics and Space A ministra ion, Washington, D. C. MEASUREMENT OF FLOW ANGULARITY AT SUPERSONIC ND HYPERSONIC SPEEDS WITH THE USE OF A CONICAL PROBE, by Frank E. S ALLEY. Sep 61, 22p. incl. illus NASA Technical ote -959 Uncl ssified reportAlso available from N A Wash. 25, D. C. as NA A Technical note D-959. SCRIP ORS yp rsonic flow, M EASUREMENT, Supersonics, Hypersonics, Conical bodies, Flight speeds, Flight testing, Cylindrical bodies. Model te t , ind tunnel models H YPERSONIC WI D UNNELS, Pressure. The characteristics of a 40 degrees half-angle cone for e suring flow angularity wer determined peri entally. Tests were conducted at a Mach number of 21 in helium with check points at Mach nu b r 3.55 in air for angles of pitc up to 5 degrees. he air tests confirm d theoretical indic ions of small or egligible Mac numb r and st-mediu ffects for the c of air and helium. The instrument is capable of measuring flow angularity at high Reynolds numbers nd peeds great r t an that necessary for hock attachment to within or - 13- egrees. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE