2024-03-28T11:46:52Z
https://nagoya.repo.nii.ac.jp/oai
oai:nagoya.repo.nii.ac.jp:00011998
2023-01-16T03:58:24Z
320:321:322
傾斜前面円柱先頭形状によるTSTO極超音速空力干渉の低減
Reduction of TSTO Hypersonic Aerodynamic Interactions Due to Diagonally-Cut Circular Cylinder Orbiter Nose
小澤, 啓伺
OZAWA, Hiroshi
花井, 勝祥
HANAI, Katsuhisa
中村, 佳朗
NAKAMURA, Yoshiaki
open access
TSTO (Two-Stage-To-Orbit)
Hypersonic Flow
Aerodynamic Interaction
Temperature Sensitive Paint (TSP)
Heat Flux
Orbiter Nose Shape
To make space activities more brisk, TSTO (Two Stage To Orbit) has been investigated worldwide as an advanced space transportation system. TSTO vehicles, which have a booster and an orbiter, have to make flight in a wide range of flight speed from subsonic to hypersonic, where they undergo aerodynamic interactions due to their combined bodies. In hypersonic flow regime, aerodynamic heating is critical, which depends on aerodynamic interaction pattern. In the present study, a delta-wing is employed as a booster and a diagonally-cut circular cylinder as an orbiter to reduce the aerodynamic interaction between these two bodies. It was found as a result of experiment that the heat flux on the head part of the diagonally-cut circular cylinder becomes about 2.4 times as large as the stagnation heat flux, while that on the delta-wing becomes about 0.5 times as large. These two values are roughly half of those in the case of a baseline combination: hemisphere-cylinder and delta-wing, which suggests that the diagonally-cut circular cylinder is promising as an orbiter head shape.
日本航空宇宙学会
2008-01-05
jpn
journal article
VoR
http://hdl.handle.net/2237/13874
https://nagoya.repo.nii.ac.jp/records/11998
1344-6460
日本航空宇宙学会論文集
56
648
8
14
https://nagoya.repo.nii.ac.jp/record/11998/files/jjsass_v56_n648_p8.pdf
application/pdf
1.5 MB
2018-02-20