DESIGN AND ANALYSIS OF WAVERIDER SCRAMJET INTAKE USING COMPUTATIONAL FLUID DYNAMICS
This thesis discussed waverider scramjet intake design and analysis for hypersonic flight conditions purposes, specifically within velocity of Mach 11.5-12.5 and altitude of 100000 ft-140000 ft. Scramjet engine generates thrust by decelerating hypersonic flow to supersonic flow passing a combustion....
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| Format: | Final Project |
| Language: | Indonesia |
| Subjects: | |
| Online Access: | https://digilib.itb.ac.id/gdl/view/74662 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | This thesis discussed waverider scramjet intake design and analysis for hypersonic flight conditions purposes, specifically within velocity of Mach 11.5-12.5 and altitude of 100000 ft-140000 ft. Scramjet engine generates thrust by decelerating hypersonic flow to supersonic flow passing a combustion. The deceleration flow is played by intake located in front of the engine. High thrust engine can be obtained by designing intake to yield supersonic flow before incoming the combustion.
Initial design and analysis are made with reference to REST engine design at hypersonic Mach number of 12 and at altitude of 120000 ft. Off design cases are then made with slightly differences in Mach number by 0.5 and altitude by 20000 ft. The design is conducted by analytical method and the design configuration will be analyzed using Computational Fluid Dynamics (CFD).
Furthermore, this thesis focused on hypersonic waverider scramjet intake design with two numbers of intake ramps and a cowl for compression at the intake. The scramjet intake overall performance will be determined by Inlet Pressure Recovery (IPR). |
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