Zobrazeno 1 - 10
of 28
pro vyhledávání: '"R. E. Sheer"'
Publikováno v:
Proceeding of International Heat Transfer Conference 3.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::9f16a88766662ab071dae8cc81937aeb
https://doi.org/10.1615/ihtc3.1800
https://doi.org/10.1615/ihtc3.1800
Publikováno v:
43rd AIAA Aerospace Sciences Meeting and Exhibit.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0fa6a6b9d35f75f1788e96a806e1ce2e
https://doi.org/10.2514/6.2005-506
https://doi.org/10.2514/6.2005-506
Publikováno v:
30th Plasmadynamic and Lasers Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6a696da671e134e35427524dcc3f8363
https://doi.org/10.2514/6.1999-3718
https://doi.org/10.2514/6.1999-3718
Publikováno v:
30th Plasmadynamic and Lasers Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::83211928d13967e6f2b5cb16e27d61f7
https://doi.org/10.2514/6.1999-3716
https://doi.org/10.2514/6.1999-3716
Publikováno v:
Fluid Dynamics Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e0bec5480f6b62eeca09702f17579ee3
https://doi.org/10.2514/6.1994-2350
https://doi.org/10.2514/6.1994-2350
Publikováno v:
Journal of Engineering for Power. 99:608-616
There is evidence that measurements of fan-rotor inlet noise taken during static test situations are at variance with aircraft engine flight data. In particular, static tests generally yield a significantly higher tone at blade passing frequency than
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0607bd9d4497e88fc17e5b665b1dd166
https://doi.org/10.1115/1.3446558
https://doi.org/10.1115/1.3446558
Publikováno v:
Journal of Engineering for Power. 105:156-166
This paper describes short duration heat transfer measurements on a flat plate and a gas turbine nozzle airfoil at high free-stream temperatures. A shock tube generated the high temperature and pressure air flow. Thin-film heat gages recorded the sur
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::100551f85c493847522182d6cd871f23
https://doi.org/10.1115/1.3227377
https://doi.org/10.1115/1.3227377
Publikováno v:
ARS Journal. 32:533-541
An investigation was conducted in a hypersonic shock tunnel to determine the local heat transfer rates for a sharp leading edge flat plate. The free stream Mach number range was 7.95 to 25.l with stagnation temperatures of approximately 2550 and 6500
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::5de83aa307916e9980fbc7ba79a1d6ef
https://doi.org/10.2514/8.6059
https://doi.org/10.2514/8.6059
Autor:
R. E. Sheer, Henry Nagamatsu
Publikováno v:
ARS Journal. 30:454-462
WADC T. B. 56-344, Office of Technical Service, U. S. Dept. of Comm., Washington, D. C , 1957. 5 El-Wakil, M. M., Uyehara, O. A. and Meyers, P. S., "A Theoretical Investigation of the Heating-Up Period of Injector Fuel Droplets Vaporizing in Air," NA
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::54e53d8962338ef48692a554d7526847
https://doi.org/10.2514/8.5118
https://doi.org/10.2514/8.5118
Publikováno v:
AIAA Journal. 10:307-313
A supersonic jet noise suppressor with 191 tubes and 191 hexagonal shrouds was investigated at jet Mach numbers of 1.4 and 0.71. Flow and acoustic data were obtained for the plain jet and various suppressor configurations. With 191 tubes the sonic lo
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f2519e33b06e01abbfbe362081f5a2d7
https://doi.org/10.2514/3.50091
https://doi.org/10.2514/3.50091