GROUND TESTING OF SCRAMJET ENGINE IN 1METER SHOCK TUNNEL AND COMPARISON WITH FLIGHT DATA

K. Snnivasan; Praveen K. Maurya; Abhishek Kumar; Amit Kumar Singh; B. Murugan; S. Pandian; S. Gnanasekar

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GROUND TESTING OF SCRAMJET ENGINE IN 1METER SHOCK TUNNEL AND COMPARISON WITH FLIGHT DATA

机译：1米冲击波隧道中飞弹发动机的地面测试及其与飞行数据的比较

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Experiments were carried out on a scaled down model o f scramjet engine with gaseous hydrogen as fuel in 1 meter combustion driven shock tunnel at VSSC.The tests were carried out at an enthalpy o f 2.6 MJ/kg,at a free stream Mach number o f 6.8 with stagnation pressures varying from 11-J9M Pa,dynamic pressure varying from 72-130 kPa and fuel to air equivalence ratio varying between 0.34-1.16.Experiments were carried out with air and nitrogen as a test gas with H2 injection to bring out the difference between reactive and non-reactive cases.For the current model scale,it was found that when combustion chamber inlet pressure (Pc) is greater than 0.1 MPa,a sharp increase in pressure downstream o f fuel injection struts is observed,whereas when Pcis.

机译：在VSSC的1米燃烧驱动冲击隧道中，以气态氢为燃料的超燃冲压发动机的按比例缩小模型进行了试验。试验以2.6 MJ / kg的焓，在自由马赫数为6.8的条件下进行。停滞压力在11-J9M Pa之间变化，动态压力在72-130 kPa之间变化，燃料与空气的当量比在0.34-1.16之间变化。以空气和氮气作为测试气体并进行H2注入进行了实验，对于当前模型规模，发现当燃烧室入口压力（Pc）大于0.1 MPa时，观察到燃料喷射支柱下游的压力急剧增加，而当Pcis时。

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来源
《Journal of Aerospace Sciences and Technologies》 |2018年第3appa期|218-226|共9页
作者
K. Snnivasan; Praveen K. Maurya; Abhishek Kumar; Amit Kumar Singh; B. Murugan; S. Pandian; S. Gnanasekar;
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作者单位

Aeronautics Entity Vikram Sarabhai Space Centre (VSSC) Department of Space;

Air Breathing Propulsion Project Vikram Sarabhai Space Centre (VSSC)Department of Space;

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原文格式 PDF
正文语种 eng
中图分类
关键词
Scramjet; Shock Tunnel Supersonic Combustion; Equivalence Ratio; Flight Test;

机译：超燃冲压发动机;冲击隧道超音速燃烧;当量比;飞行测试;

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1. GROUND TESTING OF SCRAMJET ENGINE IN 1METER SHOCK TUNNEL AND COMPARISON WITH FLIGHT DATA [J] . K. Snnivasan, Praveen K. Maurya, Abhishek Kumar, Journal of Aerospace Sciences and Technologies . 2018,第3a期

机译：1米冲击波隧道中飞弹发动机的地面测试及其与飞行数据的比较
2. FULL SCRAMJET ENGINE FLOW FIELD COMPUTATION AND FLIGHT TEST DATA COMPARISON [J] . Amit Kumar Singh, Dipankar Das, V. Ashok, Journal of Aerospace Sciences and Technologies . 2018,第3a期

机译：全挂式发动机流场计算与飞行测试数据比较
3. FULL SCRAMJET ENGINE FLOW FIELD COMPUTATION AND FLIGHT TEST DATA COMPARISON [J] . Amit Kumar Singh, Dipankar Das, V. Ashok, Journal of Aerospace Sciences and Technologies . 2018,第3Appa期

机译：全挂式发动机流场计算与飞行测试数据比较
4. Enhancement of Free Flight Force Measurement Technique for Scramjet Engine Shock Tunnel Testing [C] . Klaus Hannemann, Jan Martinez Schramm, Sebastian Karl, AIAA international space planes and hypersonic systems and technologies conference . 2017

机译：用于超燃冲压发动机冲击隧道测试的自由飞行力测量技术的增强
5. Numerical simulation of scramjet combustion in a shock tunnel. [D] . Star, Jason B. 2006

机译：冲击隧道内超燃冲压发动机燃烧的数值模拟。
6. Interlaboratory Comparison of Sample Preparation Methods Database Expansions and Cutoff Values for Identification of Yeasts by Matrix-Assisted Laser Desorption Ionization–Time of Flight Mass Spectrometry Using a Yeast Test Panel [O] . Anneloes Vlek, Anna Kolecka, Kantarawee Khayhan, 2014

机译：实验室制备样品方法数据库扩展和临界值的实验室间比较用于通过酵母辅助检测仪通过基质辅助激光解吸电离-飞行时间质谱法鉴定酵母
7. Scramjet Tests in a Shock Tunnel at Flight Mach 7, 10, and 15 Conditions [O] . Rogers, R. C., Shih, A. T., Foelsche, R. O., 2001

机译：Scramjet在7、10和15马赫飞行条件下的冲击隧道中进行测试
8. Scramjet Tests in a Shock Tunnel at Flight Mach 7, 10, and 15 Conditions [R] . Rogers, R. C., Shih, A. T., Tsai, C.-Y., 2001

机译：scramjet在飞行7,10和15飞行条件下的冲击隧道中进行测试

GROUND TESTING OF SCRAMJET ENGINE IN 1METER SHOCK TUNNEL AND COMPARISON WITH FLIGHT DATA

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