Abstract
The current work deals with a thermal design of a view port for a sub-orbital flight. Geometry of a typical sub-orbital flight was considered for this design. Using a typical suborbital flight trajectory, heat flux was estimated. For atmospheric re-entry, engineering correlations are used to estimate time varying stagnation heat flux from the trajectory data. At a time instant, CFD analysis was carried out to verify the consistency in stagnation heat flux. From CFD analysis, a factor was derived between stagnation heat flux and the heat flux at view port location. This factor was applied over the time varying stagnation heat flux to obtain transient heat flux profile on view port. A grid Independence study was performed and the grid independent results were only used in this study. Different materials were evaluated for the view port and a thermal analysis was carried out to estimate the optimum thickness requirement for each of these material using one dimensional thermal analysis.
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