Experimental and Numerical Performance Analysis of a Self-Starting Three-Dimensional Scramjet Intake
| Autor: | Andreas K. Flock, Ali Gülhan |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2017 |
| Předmět: |
Engineering
Quantitative Biology::Tissues and Organs Physics::Medical Physics Mathematics::Analysis of PDEs Aerospace Engineering Mechanical engineering 02 engineering and technology Quantitative Biology::Other 01 natural sciences 010305 fluids & plasmas Physics::Fluid Dynamics 0203 mechanical engineering 0103 physical sciences Scramjet Boiler blowdown Wind tunnel 020301 aerospace & aeronautics Computer simulation business.industry Mechanical Engineering Wind Tunnel Experiments Static pressure Mechanics CFD Analysis Fuel Technology Space and Planetary Science Airbreathing Propulsion Über- und Hyperschalltechnologien KP Intake Starting Combustion chamber business Reynolds-averaged Navier–Stokes equations |
| Popis: | In this work, a three-dimensional intake model was investigated in a blowdown wind tunnel and results were compared and complemented with Reynolds-averaged Navier–Stokes simulations. The intake model was equipped with a movable cowl with which the internal contraction ratio was set to the self-starting limit. Three different conditions were investigated: first, a v-shaped cowl geometry at a freestream Mach number of seven; second, a straight cowl geometry at a freestream Mach number of seven; and, finally, a v-shaped cowl geometry at a freestream Mach number of six. Furthermore, a one-dimensional postanalysis was performed to calculate overall engine parameters from stream-thrust-averaged intake performance parameters. Numerical results were within the experimental uncertainty, except for small displacements near separation regions. The mass capture ratio of the v-shaped cowl was slightly higher as compared to the straight cowl. When increasing the Mach number from six to seven, the specific impulse dropped from 2561 to 2100 s, respectively. For the Mach 7 configurations, a Maximum sustainable backpressure ratio of approximately 115 was measured. For the Mach 6 case, the maximum sustainable static backpressure ratio dropped to about 85. The maximum sustainable backpressure to operating backpressure ratio was around 4:1, and it was independent of the Mach number. |
| Databáze: | OpenAIRE |
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