@techreport{oai:jaxa.repo.nii.ac.jp:00043818,
 author = {近藤, 博 and 長谷川, 聡 and KONDO, Hiroshi and HASEGAWA, Satoshi},
 month = {Oct},
 note = {The small-scale model adopted in NAL TM-185 is modified and tested. The revised configuration with the diffuser annulus unchanged is of rotating-lip type with fixed-lead- ing-edge ring (auxiliary ports being shifted forward in revision), and has a highlight dia- meter 10% larger than the original one.  The test results are as follows: 1) At zero flight speed without cross wind, the total-pressure recovery attains 98% with auxiliary passages closed and 99% with auxiliary ports open, when the mean axial flow velocity equals 120 m/s at the fan face. 2) On the model with the auxiliary passages dismissed in a cross wind, a tail wind exerts more influence than head wind. When a one-ring-type ring vane is inserted into the  diffuser, the total-pressure distortion is moderated. However, the data has shown that  more research is needed., 資料番号: NALTM0235000, レポート番号: NAL TM-235},
 title = {推進エンジン用空気取入口の予備実験(続報)},
 year = {1972}
}