Abstract
Reduced-order engineering correlations for hypersonic vehicles are useful during early mission design studies and can also be used as a part of multi-fidelity modeling to reduce the number of high-fidelity simulations required. Various correlations already exist for approximating the stagnation point convective and radiative surface heat flux on hypersonic vehicles. However, there do not appear to be any correlations developed to estimate the stagnation point dust erosion rate on entry vehicles or hypersonic cruise vehicle leading-edges with sweep. This study aims to create a simple engineering correlation to give an estimate of stagnation point erosion rate due to dust impacts based on a vehicle’s size, TPS/surface material, freestream conditions, and dust loading conditions. The developed correlation was implemented for a number of Mars entry and Earth hypersonic cruise vehicle leading-edge cases and compared to higher fidelity CFD simulations. For the Mars entry cases, the correlation predicted total cumulative stagnation point erosion for six vehicles with different nose radii traveling along the ExoMars Schiaparelli capsule trajectory all within 16% error. For the Earth vehicle swept leading-edges, the correlation showed that monodispersed erosion rate due to 98.8% of individual simulated particle sizes (��_�� ≥ 2.0����) could be predicted within ±25% of the high-fidelity solution.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
