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Conceptual Design for a Dual-Bell Rocket Nozzle System Using a NASA F-15 Airplane as the Flight TestbedThe dual-bell rocket nozzle was first proposed in 1949, offering a potential improvement in rocket nozzle performance over the conventional-bell nozzle. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. In 2013 a proposal was constructed that offered a NASA F-15 airplane as the flight testbed, with the plan to operate a dual-bell rocket nozzle during captive-carried flight. If implemented, this capability will permit nozzle operation into an external flow field similar to that of a launch vehicle, and facilitate an improved understanding of dual-bell nozzle plume sensitivity to external flow-field effects. More importantly, this flight testbed can be utilized to help quantify the performance benefit with the dual-bell nozzle, as well as to advance its technology readiness level. Toward this ultimate goal, this paper provides plans for future flights to quantify the external flow field of the airplane near the nozzle experiment, as well as details on the conceptual design for the dual-bell nozzle cold-flow propellant feed system integration within the NASA F-15 Propulsion Flight Test Fixture. The current study shows that this concept of flight research is feasible, and could result in valuable flight data for the dual-bell nozzle.
Document ID
20140011268
Document Type
Conference Paper
Authors
Jones, Daniel S. (NASA Armstrong Flight Research Center Edwards, CA, United States)
Ruf, Joseph H. (NASA Marshall Space Flight Center Huntsville, AL United States)
Bui, Trong T. (NASA Armstrong Flight Research Center Edwards, CA, United States)
Martinez, Martel (NASA Armstrong Flight Research Center Edwards, CA, United States)
St. John, Clinton W. (NASA Armstrong Flight Research Center Edwards, CA, United States)
Date Acquired
September 2, 2014
Publication Date
July 28, 2014
Subject Category
Launch Vehicles and Launch Operations
Astronautics (General)
Report/Patent Number
AFRC-E-DAA-TN14964
Meeting Information
AIAA/ASME/SAE/ASEE Joint Propulsion Conference(Cleveland, OH)
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
nozzle
propulsion
F-15
conventional-bell
thrust-coefficient
PFTF
dual-bell
NPR
rocket
testbed
flight-test
nozzle-efficiency
NNPR
captive-carry
flight-research

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