書誌事項
- タイトル別名
-
- Study on Hypersonic Compression Corner Flows Using Glow Discharge-Tracer Technique
- グロー ホウデン トレーサーホウ オ モチイタ ゴク チョウオンソク アッシュク コーナーリュウ ノ ケンキュウ
この論文をさがす
抄録
In this report, we apply high frequency impulsive glow discharge technique for obtaining the flow pattern upstream of a compression corner. For purpose of comparison, schlieren visualization using high speed video camera is also performed. These experiments are carried out in a hypersonic gun tunnel at Mach number 10 and Reynolds number based on the frontal plate chord length 2.1×105. The corner angles studied are in the range from 0 to 30deg at zero incidence. Time lines are obtained successfully even for separated flow cases and the boundary layer edges visualized by the discharge-tracer technique correlate well with those defined through the schlieren images. The extent of the upstream influence becomes large with increasing corner angles and the separated boundary layer is transitional to turbulent flow for the largest angle case tested. Free interaction similarity using Newtonian theory is presented and it seems reasonable with respect to the present experimental results.
収録刊行物
-
- 日本航空宇宙学会論文集
-
日本航空宇宙学会論文集 54 (631), 337-344, 2006
一般社団法人 日本航空宇宙学会
- Tweet
キーワード
詳細情報 詳細情報について
-
- CRID
- 1390282679446979456
-
- NII論文ID
- 10019370425
-
- NII書誌ID
- AA11307372
-
- ISSN
- 24323691
- 13446460
-
- NDL書誌ID
- 8071786
-
- 本文言語コード
- ja
-
- データソース種別
-
- JaLC
- NDL
- Crossref
- CiNii Articles
-
- 抄録ライセンスフラグ
- 使用不可
