Hydrogen Film Cooling With Incident and Swept-Shock Interactions in a Mach 6.4 Nitrogen Fre.pdf
- 1、本文档共48页,可阅读全部内容。
- 2、有哪些信誉好的足球投注网站(book118)网站文档一经付费(服务费),不意味着购买了该文档的版权,仅供个人/单位学习、研究之用,不得用于商业用途,未经授权,严禁复制、发行、汇编、翻译或者网络传播等,侵权必究。
- 3、本站所有内容均由合作方或网友上传,本站不对文档的完整性、权威性及其观点立场正确性做任何保证或承诺!文档内容仅供研究参考,付费前请自行鉴别。如您付费,意味着您自己接受本站规则且自行承担风险,本站不退款、不进行额外附加服务;查看《如何避免下载的几个坑》。如果您已付费下载过本站文档,您可以点击 这里二次下载。
- 4、如文档侵犯商业秘密、侵犯著作权、侵犯人身权等,请点击“版权申诉”(推荐),也可以打举报电话:400-050-0827(电话支持时间:9:00-18:30)。
查看更多
Hydrogen Film Cooling With Incident and Swept-Shock Interactions in a Mach 6.4 Nitrogen Fre
NASA Technical Memorandum 4603
Hydrogen Film Cooling With Incident and
Swept-Shock Interactions in a Mach 6.4
Nitrogen Free Stream
George C. Olsen and Robert J. Nowak
Langley Research Center ? Hampton, Virginia
June 1995
Printed copies available from the following:
NASA Center for AeroSpace Information National Technical Information Service (NTIS)
800 Elkridge Landing Road 5285 Port Royal Road
Linthicum Heights, MD 21090-2934 Springfield, VA 22161-2171
(301) 621-0390 (703) 487-4650
Available electronically at the following URL address: /ltrs/ltrs.html
Introduction
Film cooling has been proposed as a means of ther-
mal protection to reduce the scramjet combustor wall
heating loads and the fuel mass required for regenerative
cooling alone. In this concept, some of the regeneratively
heated hydrogen fuel is injected at a supersonic velocity
parallel to the wall through small slots to provide a buffer
layer between the hot engine core flow and the structure.
In addition to thermal protection, film cooling may
improve engine performance by reducing skin friction
and providing thrust in the high Mach number operating
range. A coordinated government and industry study was
conducted (refs. 1 and 2) to define film cooling technol-
ogy for application to scramjet engines and to identify
areas that require further data. The experimental effort
reported herein is an outgrowth of this study.
Some aerothermal problems associated with hyper-
sonic flows are summarized in reference 3. These prob-
lems include determining heat fluxes in the regions of
incident-shock (two-dimensional) and swept-shock
(three-dimensional) interactions with turbulent boundary
layers. An oblique shock incident on a turbulent bound-
ary layer forms a two-dimensional flow field with a sepa-
rate flow region, a “lambda” shock structure (the incident
and separation shock combination), and a reattachment
(reflected) shock (fig. 1(a)). The interaction region
becomes steady state and the extent of the separati
您可能关注的文档
- H3C S3600 系列以太网PON OLT 交换机说明书.pdf
- Haiti-Volunteer-Packet.pdf
- Halfwidth and fullwidth forms.pdf
- halliburton 5.5in casing mutistage completion.pdf
- halliburton的发电机和无线通讯_现场实验.pdf
- Hamiltonian structure and quantization of 2+1 dimensional gravity coupled to particles.pdf
- Handling Manipulated Evidence.pdf
- Handling Failures in Human-Computer Conversation.pdf
- Hard X-ray Observations of Magnetic Cataclysmic Variables.pdf
- Harvard School of Public Health Authors.pdf
文档评论(0)