TY - JOUR
T1 - Experimental study of high-speed air intake performance by side clearance
AU - Ogura, Shogo
AU - Fujii, Manami
AU - Hoshiya, Yusuke
AU - Fujimori, Yuki
AU - Sato, Tetsuya
AU - Taguchi, Hideyuki
AU - Kojima, Takayuki
AU - Oki, Junichi
N1 - Funding Information:
The authors declare the following financial interests/personal relationships which may be considered as potential competing interests: Grant-in-Aid for Scientific Research (S), No. 20H05654.The authors acknowledge the contributions of following research team members: Mr. Suzuki and Mr. Yamauchi in ISAS/JAXA; Mr. Yokoi, Mr. Iba, Mr. Uchiyama and Mr. Seta at the Waseda University. This research was supported by Grant-in-Aid for Scientific Research (S), No. 20H05654.
Publisher Copyright:
© 2022 Elsevier Masson SAS
PY - 2022/4
Y1 - 2022/4
N2 - Japan Aerospace Exploration Agency (JAXA) and universities plan the “High Mach Integrated Control Experiment” (HIMICO), which is a hypersonic flight test by JAXA's S-520 sounding rocket. The experimental aircraft for HIMICO is powered by a ramjet engine, whose intake is a rectangular mixed compression type with a design Mach number of 5. In this research, the effects of the side clearance (SC) on the intake performance are investigated at Mach 3.4 by supersonic wind tunnel tests. The side clearances are thin slits between the 2nd and 3rd ramps and sidewalls, which is provided for driving the variable geometry intake. Three types of models with different SC widths were compared. As the results, it is found that the 2nd ramp SC, which is located upstream of the throat, causes the performance deterioration and the 3rd ramp SC, which is located downstream of the throat can expand the starting range. Hybrid SC which has only the 3rd ramp SC obtains sufficient Mass Capture Ratio (MCR) and maintains the start condition over a wider nozzle throat height range due to the air bleed from the 3rd ramp SC. However, the performance of Hybrid SC deteriorates when adding the sideslip angle, β=5°, because of a leakage from the bleed slit located between the 2nd and 3rd ramps.
AB - Japan Aerospace Exploration Agency (JAXA) and universities plan the “High Mach Integrated Control Experiment” (HIMICO), which is a hypersonic flight test by JAXA's S-520 sounding rocket. The experimental aircraft for HIMICO is powered by a ramjet engine, whose intake is a rectangular mixed compression type with a design Mach number of 5. In this research, the effects of the side clearance (SC) on the intake performance are investigated at Mach 3.4 by supersonic wind tunnel tests. The side clearances are thin slits between the 2nd and 3rd ramps and sidewalls, which is provided for driving the variable geometry intake. Three types of models with different SC widths were compared. As the results, it is found that the 2nd ramp SC, which is located upstream of the throat, causes the performance deterioration and the 3rd ramp SC, which is located downstream of the throat can expand the starting range. Hybrid SC which has only the 3rd ramp SC obtains sufficient Mass Capture Ratio (MCR) and maintains the start condition over a wider nozzle throat height range due to the air bleed from the 3rd ramp SC. However, the performance of Hybrid SC deteriorates when adding the sideslip angle, β=5°, because of a leakage from the bleed slit located between the 2nd and 3rd ramps.
KW - HIMICO
KW - Intake bleed
KW - Supersonic air intake
KW - Supersonic wind tunnel test
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U2 - 10.1016/j.ast.2022.107439
DO - 10.1016/j.ast.2022.107439
M3 - Article
AN - SCOPUS:85125874213
SN - 1270-9638
VL - 123
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 107439
ER -