Abstract:The performance and the buzz onset of a supersonic mixed-compression axisymmetric intake are experimentally investigated. Effects of the slot bleed position, angle, and width on the intake performance and on the buzz initiation at three different Mach numbers of 1.8, 2.0, and 2.2 and at a zero degree angle of attack are studied. The intake performance is assessed using the total pressure recovery, mass flow ratio, flow distortion, and bleed mass flow ratio. The results show that applying the bleed at a positio… Show more
“…However, all results in the current study are for tests with a cone without bleed. Performance of the intake with and without the boundary-layer suction has already been studied [46,47].…”
Section: B Modelmentioning
confidence: 99%
“…For every freestream Mach number and for each plug position, the data for all 62 pressure ports were collected simultaneously. All data were acquired at a sampling rate of 2.8 kHz for 1.8 s. Lowfrequency sensors were used for steady measurements and for calculation of the performance parameters of the intake such as the total pressure recovery, mass flow ratio, and static distortion [46,47]. These sensors were relatively large and could not be placed inside the model.…”
Section: Test Procedures and Location Of Sensorsmentioning
“…However, all results in the current study are for tests with a cone without bleed. Performance of the intake with and without the boundary-layer suction has already been studied [46,47].…”
Section: B Modelmentioning
confidence: 99%
“…For every freestream Mach number and for each plug position, the data for all 62 pressure ports were collected simultaneously. All data were acquired at a sampling rate of 2.8 kHz for 1.8 s. Lowfrequency sensors were used for steady measurements and for calculation of the performance parameters of the intake such as the total pressure recovery, mass flow ratio, and static distortion [46,47]. These sensors were relatively large and could not be placed inside the model.…”
Section: Test Procedures and Location Of Sensorsmentioning
“…There are porous bleed holes on the upper and lower walls of the test section that can stabilize and control wind tunnel shock and other reflected waves as well as controlling the boundary layer thickness. Sidewall windows of the test section make it possible to observe the flow and shock pattern by means of Schlieren or Shadowgraph visualization systems (Soltani, Younsi, and Farahani 2015;. The current wind tunnel tests were conducted for various AOA at a free stream Mach number of ∞ =1.65.…”
An extensive experimental investigation to study the effects of angle of attack (AOA) on the performance of a body-integrated supersonic inlet has been carried out. The present inlet, known as Diverterless Supersonic Inlet (DSI), is utilized with a three-dimensional bump to provide both supersonic flow compression and boundary layer diversion. Experiments were conducted at the presence of a typical fore-body including an elliptical nose to further contemplate the effects of fore-body geometry on the approaching flow. All tests were conducted at a constant free stream Mach number, ∞ = 1.65 zero degrees angle of sideslip (AOS), and at various angles of attack (AOA) ranging from-2 to 6 degrees. The results showed that the present DSI had acceptable performance characteristics for all ranges of AOA tested. It should be noted that the present DSI does not have any moving, adjustable or auxiliary mechanisms as such systems or mechanism are used to improve the performance of an inlet.
“…Figure 20.Performance curves of the intake for various bleed configurations at design Mach number of 2.0: (a) variation of bleed position, (b) variation of bleed angle, (c) variation of bleed entrance width. 56 Figure 21.Shadowgraph pictures ahead of the intake for base cone (right), cone with bleed slant angle of 45° (middle), and cone with bleed slant angle of 90° (left) at M ∞ = 2.0. 56 …”
Section: Effects Of Bleed On the Intake Performancementioning
The paper summarizes recent developments in boundary layer suction for high-speed air intakes. Bleed has been efficiently used in supersonic and hypersonic intakes for three primary reasons: to improve the performance of the intake, to reduce the starting Mach number of the intake, and to postpone the onset of buzz oscillations. A bleed system has many characteristics such as the bleed entrance and exit areas, bleed entrance slant angle and position, and bleed type (slot or porous and ram-scoop or flush). Each of these parameters has significant impacts on the intake performance and stability that have been reviewed in this study. In addition, the effectiveness of other flow control methods has been compared with the bleed method.
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