TY  - JOUR
AV  - none
N2  - Designers of the aero engines are in quest of maintaining the pressure as high as possible at the face of the compressor, with air velocity not higher than 0.8 Mach. Reduction of the flow from supersonic to such speed is combined with pressure reduction. This paper presents results from coupled techniques to solve for the flow field of double wedge spiked supersonic intake. The selected spike has 4° forebody wedge angle and the second ramp angle is 8°. The external part of the flow was solved analytically while the internal part was solved numerically by finite volume technique. The analysis was carried out at different Mach numbers (1.4, 1.8, 2.2, 2.4, and 3) and different angles of attack (0°, 6°, and 12°). The procedure is validated and the results are presented in terms of the pressure recovery at the face of the compressor. The results have shown that generally the pressure recovery decreases by increasing of incidence angle. The non-zero incidence was found to produce noticeable difference in pressure distribution at the face of the compressor. This became considerably effective at incidences leading to detached shocks at the leading edge of the spike. © (2012) Trans Tech Publications, Switzerland.
JF  - Applied Mechanics and Materials
VL  - 225
KW  - Aero-engine; Air velocities; Angles of attack; Double wedge; Finite volume technique; Incidence angles; Leading edge; Pressure recovery; Pressure reduction; Ramp angle; Spike; Supersonic inlets; Supersonic intake; Wedge angle
KW  -  Air; Aircraft engines; Compressible flow; Compressors; Intake systems; Mach number; Supersonic flow
KW  -  Flow fields
EP  - 72
CY  - Kuala Lumpur
UR  - https://www.scopus.com/inward/record.uri?eid=2-s2.0-84871112577&doi=10.4028%2fwww.scientific.net%2fAMM.225.67&partnerID=40&md5=fcd85bd09d6b6eb3e222890914c33ac1
N1  - cited By 0; Conference of AEROTECH IV - 2012 ; Conference Date: 21 November 2012 Through 22 November 2012; Conference Code:94395
SP  - 67
ID  - scholars2384
TI  - Coupled analytical-numerical procedure to solve the double wedge spiked supersonic intake flow field
SN  - 16609336
Y1  - 2012///
A1  - Al-Kayeim, H.H.
A1  - Salih, T.W.
A1  - Govindasamy, D.
ER  -