Zobrazeno 1 - 10
of 13
pro vyhledávání: '"Robert D. Bittner"'
Publikováno v:
Journal of Spacecraft and Rockets. 47:922-934
The successful Mach 7 and 10 flights of the first fully integrated scramjet propulsion systems by the Hyper-X (X-43A) program have provided the means with which to verify the original design methodologies and assumptions. As part of Hyper-X s propuls
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0fd1f6d9be7bdcbc04088a89fd051ca1
https://doi.org/10.2514/1.45889
https://doi.org/10.2514/1.45889
Integrated Aeropropulsive Computational Fluid Dynamics Methodology for the Hyper-X Flight Experiment
Autor:
Charles E. Cockrell, Tom N. Jentink, Arthur D. Dilley, Abdelkader Frendi, Walter C. Engelund, Robert D. Bittner
Publikováno v:
Journal of Spacecraft and Rockets. 38:836-843
Computational e uid dynamics tools have been used extensively in the analysis and development of the X-43A Hyper-X Research Vehicle. A signiecant element of this analysis is the prediction of integrated vehicle aeropropulsive performance,which includ
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::90551c479d018b7d2c9caf2aac64eb4b
https://doi.org/10.2514/2.3773
https://doi.org/10.2514/2.3773
Publikováno v:
Journal of Propulsion and Power. 11:409-418
A method for estimating the axial distribution of thrust performance potential in a supersonic combustor is described. A complementary technique for illustrating the spatial evolution and distribution of thrust potential and loss mechanisms in reacti
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c15cc92cf4a76b245f2b03e3f594c70d
https://doi.org/10.2514/3.23859
https://doi.org/10.2514/3.23859
Publikováno v:
Journal of Propulsion and Power. 8:890-899
The establishment of a quasi-steady flow in a generic scramjet combustor was studied for the case of a time varying inflow to the combustor. Such transient flow is characteristic of the reflected shock tunnel and expansion tube test facilities. Sever
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cd175e67f713c6b73ef22c964214fe0e
https://doi.org/10.2514/3.23566
https://doi.org/10.2514/3.23566
Publikováno v:
38th Fluid Dynamics Conference and Exhibit.
The successful Mach 7 and 10 flights of the first fully integrated scramjet propulsion systems by the Hyper-X (X-43A) program have provided the means with which to verify the original design methodologies and assumptions. As part of Hyper-X s propuls
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0f1fb4b66d1f6d78cb3702f98563cde4
https://doi.org/10.2514/6.2008-3736
https://doi.org/10.2514/6.2008-3736
Publikováno v:
22nd Applied Aerodynamics Conference and Exhibit.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6f0d35351dc215a89ddff49ba855f741
https://doi.org/10.2514/6.2004-5385
https://doi.org/10.2514/6.2004-5385
Publikováno v:
25th Plasmadynamics and Lasers Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1ca3747305c609451527b77614a02cc1
https://doi.org/10.2514/6.1994-2518
https://doi.org/10.2514/6.1994-2518
Publikováno v:
29th Joint Propulsion Conference and Exhibit.
Numerical simulations of 3D turbulent mixing and reacting flows have been systematically evaluated by comparison with experimental data and other numerical solutions to provide confidence in the General Aerodynamic Simulation Program (GASP) code vers
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a9e953b51e74a7d1cc310379cbb188c5
https://doi.org/10.2514/6.1993-1973
https://doi.org/10.2514/6.1993-1973
Publikováno v:
28th Joint Propulsion Conference and Exhibit.
A simple method for predicting the axial distribution of supersonic combustor thrust potential is described. A complementary technique for illustrating the spatial evolution and distribution of thrust potential and loss mechanisms in reacting flows i
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f607f229831ba0f41ac4c870dc26365a
https://doi.org/10.2514/6.1992-3287
https://doi.org/10.2514/6.1992-3287
Publikováno v:
3rd International Aerospace Planes Conference.
Three-dimensional finite rate chemistry solutions are performed on a single fuel injector configuration. The results are compared with limited experimental data obtained from the HYPULSE expansion tube facility at simulated flight Mach 17 flow condit
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d5779e962e9a0d96b5686f45c89ac766
https://doi.org/10.2514/6.1991-5093
https://doi.org/10.2514/6.1991-5093