Michael K. Smart
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View article: Testing of DLR C/C-SiC and C/C for HIFiRE 8 Scramjet Combustor
Testing of DLR C/C-SiC and C/C for HIFiRE 8 Scramjet Combustor Open
Ceramic Matrix Composites (CMCs) have been proposed for use as lightweight hot structures in scramjet combustors. Previous studies have calculated significant weight savings by utilizing CMCs (active and passive) versus actively cooled met…
View article: Testing of DLR C/C-SiC for HIFiRE 8 Scramjet Combustor
Testing of DLR C/C-SiC for HIFiRE 8 Scramjet Combustor Open
Ceramic Matrix Composites (CMCs) have been proposed for use as light-weight hot
\nstructures in scramjet combustors. Previous studies have calculated significant weight
\nsavings by utilizing CMCs (active and passive) versus actively coole…
View article: Chemical Rocket Propulsion
Chemical Rocket Propulsion Open
1Department of Aerospace Engineering, Ryerson University, Toronto, ON, Canada M5B 2K3 2Aerophysics Branch, Air Force Research Laboratory, Edwards AFB, CA 93524, USA 3Dipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torin…
View article: Free-Jet Testing of a REST Scramjet at Off-Design Conditions
Free-Jet Testing of a REST Scramjet at Off-Design Conditions Open
Scramjet flowpaths employing elliptical combustors have the potential to improve structural efficiency and performance relative to those using planar geometries. NASA Langley has developed a scramjet flowpath integrated into a lifting body…
View article: Computational investigation of the performance and back-pressure limits of a hypersonic inlet
Computational investigation of the performance and back-pressure limits of a hypersonic inlet Open
A computational analysis of Mach 6.2 operation of a hypersonic inlet with rectangular-to-elliptical shape transition has been performed. The results of the computations are compared with experimental data for cases with and without a manua…
View article: CIAM/NASA Mach 6.5 scramjet flight and ground test
CIAM/NASA Mach 6.5 scramjet flight and ground test Open
The Russian Central Institute of Aviation Motors (CIAM) performed a flight test of a CIAM-designed, hydrogen-cooled/fueled dual-mode scramjet engine over a Mach number range of approximately 3.5 to 6.4 on February 12, 1998, at the Sary Sha…
View article: Measurements of supersonic wing tip vortices
Measurements of supersonic wing tip vortices Open
An experimental survey of supersonic wing tip vortices has been conducted at Mach 2.5 using small performed 2.25 chords down-stream of a semi-span rectangular wing at angle of attack of 5 and 10 degrees. The main objective of the experimen…