@techreport{oai:jaxa.repo.nii.ac.jp:00043769,
 author = {近藤, 博 and 石賀, 保正 and KOND0, Hiroshi and ISHIGA, Yasumasa},
 month = {Sep},
 note = {Some results of low-speed performance tests with a smaIl-scale model for turbo- fan engine are presented and discussed. The results are as follows: 1) At zero flight speed, the total pressure recovery with a given opening area of  the auxiliary inlet ports decreased as the mean axial flow velocity V2 at the fan  face increased. 2) In the test range of flight speed Vo, the total pressure recovery with a given  opening area of the auxiliary inlet ports increased up to 99% and more as the value of Vo/V2 increased. 3) At any tested combination of Vo with V2, the total pressure recovery increased  as the number of the closed auxiliary inlet ports decreased. 4) The observed upstream flow behavior, inlet distortion, and surface static pressure distribution as the function of the value of Vo/V2 are presented and discussed  taking the effects of ground clearance and attack angle also into consideration., 資料番号: NALTM0185000, レポート番号: NAL TM-185},
 title = {推進エンジン用空気取入口の予備実験},
 year = {1970}
}