Performance Study of a Supersonic Inlet in the Presence of a Heat Source
Year
: 2011
Abstract: The flow over a supersonic inlet has been investigated experimentally and numerically at a
free stream Mach number of 2 and a zero degree angle of attack. Wind tunnel tests were performed to
obtain the performance parameters of the inlet and were used as a baseline and validation tools for the
numerical code. A heat source was added to the flow field at a distance ahead of the inlet. The effect of
heat source addition on the main performance parameters of the inlet is investigated numerically. Results
show that the heat source considerably reduces drag coefficient; however, its effect on pressure recovery is not favorable. This unfavorable effect was then minimized by controlling heat source parameters, such as its location, size and shape. For the optimum condition, drag coefficient reduces considerably, inlet mass flow rate increases, but pressure recovery slightly decreases.
free stream Mach number of 2 and a zero degree angle of attack. Wind tunnel tests were performed to
obtain the performance parameters of the inlet and were used as a baseline and validation tools for the
numerical code. A heat source was added to the flow field at a distance ahead of the inlet. The effect of
heat source addition on the main performance parameters of the inlet is investigated numerically. Results
show that the heat source considerably reduces drag coefficient; however, its effect on pressure recovery is not favorable. This unfavorable effect was then minimized by controlling heat source parameters, such as its location, size and shape. For the optimum condition, drag coefficient reduces considerably, inlet mass flow rate increases, but pressure recovery slightly decreases.
Keyword(s): Supersonic inlet,Heat source,Drag coefficient,Pressure recovery,Mass flow rate
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Performance Study of a Supersonic Inlet in the Presence of a Heat Source
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| contributor author | M.R. Soltani | en |
| contributor author | M. Farahani | en |
| contributor author | جواد سپاهی یونسی | en |
| contributor author | Javad Sepahi-Younsi | fa |
| date accessioned | 2020-06-06T13:27:57Z | |
| date available | 2020-06-06T13:27:57Z | |
| date issued | 2011 | |
| identifier uri | https://libsearch.um.ac.ir:443/fum/handle/fum/3355968?locale-attribute=en | |
| description abstract | The flow over a supersonic inlet has been investigated experimentally and numerically at a free stream Mach number of 2 and a zero degree angle of attack. Wind tunnel tests were performed to obtain the performance parameters of the inlet and were used as a baseline and validation tools for the numerical code. A heat source was added to the flow field at a distance ahead of the inlet. The effect of heat source addition on the main performance parameters of the inlet is investigated numerically. Results show that the heat source considerably reduces drag coefficient; however, its effect on pressure recovery is not favorable. This unfavorable effect was then minimized by controlling heat source parameters, such as its location, size and shape. For the optimum condition, drag coefficient reduces considerably, inlet mass flow rate increases, but pressure recovery slightly decreases. | en |
| language | English | |
| title | Performance Study of a Supersonic Inlet in the Presence of a Heat Source | en |
| type | Journal Paper | |
| contenttype | External Fulltext | |
| subject keywords | Supersonic inlet | en |
| subject keywords | Heat source | en |
| subject keywords | Drag coefficient | en |
| subject keywords | Pressure recovery | en |
| subject keywords | Mass flow rate | en |
| journal title | Scientia Iranica | en |
| journal title | Scientia Iranica | fa |
| pages | 375-382 | |
| journal volume | 18 | |
| journal issue | 3 | |
| identifier link | https://profdoc.um.ac.ir/paper-abstract-1054294.html | |
| identifier articleid | 1054294 |