This paper presents the preliminary results of a research investigation intended to identify the most appropriate compressibility correction approach for the Flamelet Progress/Variable (FPV) formulation. This topic is vital for the design and advancement of hypersonic airbreathing vehicles. Consequently, there is a high demand for accurate, versatile, and computationally cost-effective methods for simulating supersonic combustion. This paper discusses the Flamelet Progress/Variable (FPV) formulation, which was utilized to simulate a reacting jet injection in a supersonic crossflow. The preliminary results presented in this paper are intended to show that the FPV formulation has been implemented in a well-established computational fluid dynamics (CFD) code. Additionally, we observed that the procedure to ignite the flow field in a FPV formulation is not trivial, and should be given more attention.
|Original language||English (US)|
|Title of host publication||2018 Joint Propulsion Conference|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2018|
|Event||54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018 - Cincinnati, United States|
Duration: Jul 9 2018 → Jul 11 2018
|Name||2018 Joint Propulsion Conference|
|Conference||54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018|
|Period||7/9/18 → 7/11/18|
Bibliographical noteFunding Information:
This work was supported by a NASA Space Technology Research Fellowship.
© 2018, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.