The effectiveness of slot film cooling of a flat plate in a Mach 6.4 flow with and without incident and swept oblique shock interactions was experimentally investigated. Hydrogen was the primary coolant gas, although some tests were conducted using helium as the coolant. Tests were conducted in the Calspan 48-Inch Shock Tunnel with a nitrogen flow field to preclude combustion of the hydrogen coolant gas. A two-dimensional highly instrumented model developed in a previous test series was used. Parameters investigated included coolant mass flow rate, coolant gas, local free-stream Reynolds number, incident oblique shock strength, and a swept oblique shock. Both gases were highly effective coolants in undisturbed flow; however, both incident a...
Film cooling is investigated on a flat plate both numerically and experimentally. Conical shaped fil...
In this thesis, a numerical study of film cooling in hypersonic laminar and turbulent flows has been...
Hypersonic vehicle design requires mitigation of the high heat fluxes present in regions of shock-wa...
Effects of flow turning, flow acceleration, and supersonic flow on film cooling were determined expe...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
Experimental studies have been conducted to examine slot film cooling effectiveness and the interact...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
Cooling experiments are performed by the DLR Institute of Space Propulsion, applying a transpiration...
Experimental film cooling data obtained during exploratory testing with an axisymmetric plug nozzle ...
Experimental studies have been conducted to examine slot film cooling effectiveness and the interact...
One of the main challenges concerning scramjet propulsion systems is the efficient and sufficient co...
Film cooling is generally considered as a promising active cooling technology for developing thermal...
Film cooling is generally considered as a promising active cooling technology for developing thermal...
Film cooling is investigated on a flat plate both numerically and experimentally. Conical shaped fil...
In this thesis, a numerical study of film cooling in hypersonic laminar and turbulent flows has been...
Hypersonic vehicle design requires mitigation of the high heat fluxes present in regions of shock-wa...
Effects of flow turning, flow acceleration, and supersonic flow on film cooling were determined expe...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
Experimental studies have been conducted to examine slot film cooling effectiveness and the interact...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
High pressure turbine stages work in transonic regimes and then shock waves, shed by the trailing ed...
Cooling experiments are performed by the DLR Institute of Space Propulsion, applying a transpiration...
Experimental film cooling data obtained during exploratory testing with an axisymmetric plug nozzle ...
Experimental studies have been conducted to examine slot film cooling effectiveness and the interact...
One of the main challenges concerning scramjet propulsion systems is the efficient and sufficient co...
Film cooling is generally considered as a promising active cooling technology for developing thermal...
Film cooling is generally considered as a promising active cooling technology for developing thermal...
Film cooling is investigated on a flat plate both numerically and experimentally. Conical shaped fil...
In this thesis, a numerical study of film cooling in hypersonic laminar and turbulent flows has been...
Hypersonic vehicle design requires mitigation of the high heat fluxes present in regions of shock-wa...