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Numerical simulations of the superdetonative ram accelerator combusting flow fieldThe effects of projectile canting and fins on the ram accelerator combusting flowfield and the possible cause of the ram accelerator unstart are investigated by performing axisymmetric, two-dimensional, and three-dimensional calculations. Calculations are performed using the INCA code for solving Navier-Stokes equations and a guasi-global combustion model of Westbrook and Dryer (1981, 1984), which includes N2 and nine reacting species (CH4, CO, CO2, H2, H, O2, O, OH, and H2O), which are allowed to undergo a 12-step reaction. It is found that, without canting, interactions between the fins, boundary layers, and combustion fronts are insufficient to unstart the projectile at superdetonative velocities. With canting, the projectile will unstart at flow conditions where it appears to accelerate without canting. Unstart occurs at some critical canting angle. It is also found that three-dimensionality plays an important role in the overall combustion process.
Document ID
19930066000
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Soetrisno, Moeljo
(NASA Headquarters Washington, DC United States)
Imlay, Scott T.
(NASA Headquarters Washington, DC United States)
Roberts, Donald W.
(Amtec Engineering, Inc. Bellevue, WA, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 93-2185
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: ASME, ASEE, SAE, AIAA
Accession Number
93A49997
Distribution Limits
Public
Copyright
Other

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