Experimental investigations of curved fin rocket
Also available in printed version
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| Format: | Bachelor thesis |
| Language: | English |
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Universiti Teknologi Malaysia
2025
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| Online Access: | https://utmik.utm.my/handle/123456789/55431 |
| Abstract | Abstract here |
| _version_ | 1854975070806474752 |
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| author | Ng, Qi Yao |
| author2 | Md. Nizam Dahalan, supervisor |
| author_facet | Md. Nizam Dahalan, supervisor Ng, Qi Yao |
| author_sort | Ng, Qi Yao |
| description | Also available in printed version |
| format | Bachelor thesis |
| id | utm-123456789-55431 |
| institution | Universiti Teknologi Malaysia |
| language | English |
| publishDate | 2025 |
| publisher | Universiti Teknologi Malaysia |
| record_format | dspace |
| record_pdf | Abstract |
| spelling | utm-123456789-554312025-08-21T00:41:36Z Experimental investigations of curved fin rocket Ng, Qi Yao Md. Nizam Dahalan, supervisor Mechanical engineering Also available in printed version Experimental or wind tunnel testing is always the choice for aerodynamicists to obtain reliable results on aerodynamic characteristics of rockets. The experiment usually obtains aerodynamic forces and moments as a function of angle of attack and Mach number. The general geometry design of conventional rockets or missiles is made of nose, body, fins or wings and boattail. This study evaluates and investigates the aerodynamic characteristics of a conventional rocket with conical nose, slender cylindrical body with no boattail, but with four unconventional cruciform fins which are the curved fins (or wrap-around fins). The rocket configurations for this study include fin alone, axisymmetric body-alone and fin-body (body-tail) for analytical analysis using USAF stability and control Datcom, while only fin-body configuration for wind tunnel testing. The aerodynamic forces and moments under investigation were lift, drag and pitching moment coefficients. The test configurations for analytical analysis include 0° to 25° angles of attack at low subsonic speeds of 20m/s, 40m/s and 68m/s. Meanwhile, test configurations for experiment include 0° to 25° angles of at low subsonic speeds of 20m/s to 50m/s. Reynolds sweep include 10m/s to 68m/s at 0° angle of attack. For the fin-body configuration detailed in this study, USAF Datcom predicted lift coefficients with minimal error, but for most cases, USAF Datcom was not effective in predicting drag and pitching moment coefficients. Finally, from comparison of wind tunnel data between conventional missiles or rockets with similar specifications and geometries obtained from other researchers and the curved fin rocket shows reasonable trend for lift, drag and pitching moment coefficients snhas UTM 143 p. Project Paper (Sarjana Muda Kejuruteraan (Mekanikal - Aeronautik)) - Universiti Teknologi Malaysia, 2015 2025-03-17T03:55:21Z 2025-03-17T03:55:21Z 2015 Bachelor thesis https://utmik.utm.my/handle/123456789/55431 valet-20170131-161924 vital:94523 ENG Closed Access UTM Complete Unpublished application/pdf Universiti Teknologi Malaysia |
| spellingShingle | Mechanical engineering Ng, Qi Yao Experimental investigations of curved fin rocket |
| thesis_level | Other |
| title | Experimental investigations of curved fin rocket |
| title_full | Experimental investigations of curved fin rocket |
| title_fullStr | Experimental investigations of curved fin rocket |
| title_full_unstemmed | Experimental investigations of curved fin rocket |
| title_short | Experimental investigations of curved fin rocket |
| title_sort | experimental investigations of curved fin rocket |
| topic | Mechanical engineering |
| url | https://utmik.utm.my/handle/123456789/55431 |
| work_keys_str_mv | AT ngqiyao experimentalinvestigationsofcurvedfinrocket |