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 |
| الملخص: | 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 recovery of intake,
surface correction of cone was attempted. By using taper plug different blockage
area of exit were obtained to locate normal shock in throat for minimum loss of
pressure. Redesign of model, pressure instrumentation, principle of intake operation
and data analysis are covered in detail in the thesis. Results of pressure values
showed good agreement with simple 1 - D compressible flow calculations. |
|---|