Improving inlet performance of turbo-ramjet engine by using surface correction
In this study axisymmetric supersonic intake model was tested at Mach number of 4. The intake geometry of SR-71 supersonic aircraft was used here for testing a scale model. Static and total pressure measurements in the duct were used to observe shock effect on internal flow. To improve pressure r...
محفوظ في:
| المؤلف الرئيسي: | |
|---|---|
| مؤلفون آخرون: | |
| التنسيق: | Thesis-Master by Coursework |
| اللغة: | English |
| منشور في: |
Nanyang Technological University
2021
|
| الموضوعات: | |
| الوصول للمادة أونلاين: | https://hdl.handle.net/10356/146359 |
| الوسوم: |
إضافة وسم
لا توجد وسوم, كن أول من يضع وسما على هذه التسجيلة!
|
| المؤسسة: | Nanyang Technological University |
| اللغة: | English |