Abstract
In cooperation with the DLR Institute of Space Propulsion Lampoldshausen, a cold flow linear aerospike nozzle with four different plugs utilizing thrust vector control through secondary fluid injection has been developed for testing at P6.2.The two main goals of this measurement set up were demonstrated in a pre-test: surface pressure measurements and flow phenomena visualization. During a test run with the reference plug (without secondary injection), the principle working function was verified and critical issues identified. The causes of these problems are analyzed, solutions discussed and implemented. This lays the foundation for a successful subsequent measurement campaign.
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