Design and Aerodynamic Analysis of a Rocket Nose Cone with Specific Fineness Ratio

The design of nose cones of rockets has attracting more attention with the developing rocket technology. It is a necessity to design the nose cone that best suits both the physical characteristics of the rocket and the flight parameters to increase flight performance. In this study, nose cone design and aerodynamic analysis for a subsonic rocket are discussed. The geometric design was handled and the tangent ogive, which is the most suitable nose cone geometry for the rocket planned to be produced, was obtained. Depending on the flight parameters, the optimal cone length was calculated and then the entire cone geometry was created. As a result, a tangent ogive nose cone with a fineness ratio of 3.33 was obtained. Through Newton flow theory, aerodynamic coefficients were computed numerically and their variations according to specific parameters were examined. For the nose cone, which will be exposed to high drag during flight, aerodynamic heating has been examined by considering the flight parameters. Thermal analysis was made according to flight data suitable for the rocket under construction, and stagnation/recovery temperatures were computed. By examining the variation of the temperature according to flight parameters, materials that can be used in nose cone production were discussed.