Rocket Nozzles
Nozzle Shapes
Radial Out-Flow
Radial In-Flow
Altitude Compensation
Performance Losses
Advantages & Disadvantages
In 1996, NASA committed itself to the development of a revolutionary new launch vehicle, the X-33. To be successful, this vehicle would require significant advances in rocketry technology, not the least of which are the linear aerospike engines. As we have seen, the strength of this type of engine is its ability to adjust to varying operating conditions resulting in improved off-design performance as compared with traditional converging-diverging nozzles like the bell. While the advantages of this nozzle have been recognized since the 1950s, it has never been utilized in rockets because of the lack of flight-test data and the perceived high risk of using an untried design. Hopefully, this deficiency will soon be rectified allowing the potential of the aerospike engine to be realized.

With NASA's decision to cancel the X-33 after its contract with Lockheed Martin expired in March 2001, the future of not only the aerospike engine, but of the entire single-stage-to-orbit concept remains unclear. However, even if the X-33 never flies, the research conducted by NASA and the Rocketdyne division of Boeing to develop aerospike engines of sufficient performance and reliability to be used on an actual flight vehicle cannot be underestimated.

Comparison of the X-33 and VentureStar vehicles

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