coverPage.png
  • Mario Javier Rincon Perez
4. term, Energy Engineering, Master (Master Programme)
The future of rocket reusability and space democratisation currently relies in the effective use of Supersonic Retropropulsion (SRP) to return rocket stages to Earth. This thesis makes a specific study of compressible flows applied to a spacecraft's re-entry burn into Earth's atmosphere.
Due to SRP complex flow structure, an accurate study is performed by means of Computational Fluid Dynamics (CFD). Furthermore, the potential of the open source software OpenFOAM is tested and compared to the existing validation results from CFD and experimental SRP. Hence, the results of a CFD SRP simulation of a 60$^{\circ}$ sphere cone geometry, running a sweep of five different thrust values is performed. The results are matched and compared with the available experimental and computational studies available.
It has been found that OpenFOAM by means of its solver \textit{rhoCentralFoam} is capable to simulate the physics involving SRP. With a very inexpensive grid, flow structures and pressure field are captured with marginal accuracy, however, to enhance and fully validate its use for SRP applications, further research has to be performed due to the significant inaccuracies yielded in the pressure distribution.
SpecialisationThermal Energy and Process Engineering
LanguageEnglish
Publication date1 Jun 2018
Number of pages81

Images

validationData.png
Standoff data
theoreticalValidation.png
Isentropic nozzle validation
schlierenExpFlow.png
Experimental BFI flow
SchlierenAll.png
Schlieren contours for different thrust coefficients
Schlieren404Coarse.png
Schlieren contour con thrust coefficient 4.04
Schlieren047Fine.png
Schlieren contour for thrust coefficient 0.47
pShockValidation.png
Validation of rhoCentralFoam for a de Laval nozzle with a normal shock in the diffuser
MaAll.png
Mach number contours for different thrust coefficients
Ma047Fine.png
Mach number contour for thrust coefficient 0.47
Ma2Coarse.png
Mach number contour for thrust coefficient 2.00
lowCp.png
Pressure coefficient validation for low thrust cases
highCp.png
Pressure coefficient validation for high thrust cases
ExpJPR.png
Experimental JPR flow
BCschematic.png
Schematic of simulated geometry
SRPdefinition.png
Definition of SRP flow
ID: 280250623