Aerodynamic Characteristics of Different Rocket Fin Configurations

As orbital launchers spring up with novel designs that enhance reusability, it is important to create convenient methods for testing new spacecraft concepts. To study the effects of different fin types on rocket flight, both in forward and reverse flow, a static model of a rocket was designed, built, and tested for the NCSU Low-Speed Wind Tunnel. The model was built with easily interchangeable sections, each with varying characteristics to maximize testing capabilities. All sections were 3D-printed to allow for rapid and accurate development of new configurations. The baseline rocket model was derived from existing literature in order to verify the accuracy of the aerodynamic results. Future developments of the model may focus on adding elements like actuators and pressure sensors to enhance the quality and quantity of data gathered for each test.

Students

• Michael Barton

Publications

• Barton, M. and Narsipur. S., “Aerodynamic Characteristics of Different Rocket Fin Configurations”, presented at the AIAA Region II Student Conference, Cocoa Beach, FL