Zobrazeno 1 - 10
of 16
pro vyhledávání: '"Donald C. Howe"'
Publikováno v:
49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
Over the past decade, Gulfstream Aerospace Corporation has published on several methods for tailoring the shape of the nacelle for reducing its profile and contribution to the sonic boom signature of an aircraft traveling at supersonic speed. Through
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::89a0b30f7221456cf43051a741cff366
https://doi.org/10.2514/6.2013-3678
https://doi.org/10.2514/6.2013-3678
Autor:
Donald C. Howe
Publikováno v:
29th AIAA Applied Aerodynamics Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::69721fd39305f0ca778ddf2cea278ca0
https://doi.org/10.2514/6.2011-3336
https://doi.org/10.2514/6.2011-3336
Publikováno v:
29th AIAA Applied Aerodynamics Conference.
1 Aero/Performance Specialist, Supersonic Technology Development, P.O. Box 2206 M/S R-07, AIAA Associate Fellow. 2 Applied Aerodynamics, Supersonic Technology Development, P.O. Box 2206 M/S R-07, AIAA Senior Member 3 Applied Aerodynamics Technical Fe
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6d291d46175111429f61ed7d127f4395
https://doi.org/10.2514/6.2011-3331
https://doi.org/10.2514/6.2011-3331
Publikováno v:
39th AIAA Fluid Dynamics Conference.
Computational simulations have been used to study a new low-boom, axisymmetric, external compression supersonic inlet with an on-design Mach number of 1·7. The inlet incorporates a relaxed compression surface with a near-zero cowl angle to help redu
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::054ac51fe7f38054329c8e8353660316
https://doi.org/10.2514/6.2009-4210
https://doi.org/10.2514/6.2009-4210
Publikováno v:
46th AIAA Aerospace Sciences Meeting and Exhibit.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e04e9795deba53b5a4bbf8603dd8cf09
https://doi.org/10.2514/6.2008-128
https://doi.org/10.2514/6.2008-128
Publikováno v:
46th AIAA Aerospace Sciences Meeting and Exhibit.
The Quiet Spike is a concept developed by Gulfstream Aerospace Corporation that breaks up the sonic boom generated by an aircraft traveling at supersonic speeds. The concept employs a structural boom that extends forward from the fuselage. Spaced alo
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1f70b25637d504d85b24645546bfcab6
https://doi.org/10.2514/6.2008-125
https://doi.org/10.2514/6.2008-125
Publikováno v:
46th AIAA Aerospace Sciences Meeting and Exhibit.
The Gulfstream Quiet Spike is a telescoping forward fuselage extension that alters the bow shock of the classic N-wave pressure signature generated by aircraft traveling at supersonic speeds. The bow shock is broken up into sequence of weak shocks th
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::5164893d4876b9bf3a9a4f9bb2965d30
https://doi.org/10.2514/6.2008-124
https://doi.org/10.2514/6.2008-124
Publikováno v:
46th AIAA Aerospace Sciences Meeting and Exhibit.
The OVERFLOW code was used to calculate the flow field for a family of five relaxed compression inlets, which were part of a screening study to determine a configuration most suited to the application of microscale flow control technology as a replac
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::2886e1eb80fe21e4c14b478d58320619
https://doi.org/10.2514/6.2008-92
https://doi.org/10.2514/6.2008-92
Publikováno v:
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
An alternative inlet design method employing isentropic relaxed compression has been developed by Gulfstream Aerospace Corporation for improving net propulsion system performance and reducing sonic boom strength. To substantiate results from prior an
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::bc3afc6cbdecaaea6a78998bb156bdea
https://doi.org/10.2514/6.2007-5066
https://doi.org/10.2514/6.2007-5066
Publikováno v:
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
A family of five axisymmetric external compression inlets was tested at Mach 1.97 in the 1-ft ×1-ft supersonic wind tunnel at the NASA Glenn Research Center. All five inlets shared the same external compression surface; they differed only in subsoni
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e4bafb5b0767d4e59b2249fe2c20263b
https://doi.org/10.2514/6.2007-5073
https://doi.org/10.2514/6.2007-5073