Return to Article Details Analytical Solution to the Steady Navier-Stokes Equation for a Supersonic Cone in the Area of Boundary Layer Behind the Shock Wave by Means Tunnel Mathematics Download Download PDF
© 2023 - 2025 Acceleron Aerospace Journal || Acceleron Aerospace Sciences Private Limited, Kundalahalli, Brookefield, Karnataka, India, Postal Code: 560037 || CIN - U72100KA2023PTC175186 ||All Rights Reserved || Acceleron Aerospace Journal grants CC BY 4.0 International License, allowing free sharing, adaptation, and redistribution of articles while guaranteeing plagiarism-free content. Copyrighted materials are acknowledged, and fair use guidelines permit partial reproduction with proper attribution. For inquiries, you can contact at connect@acceleron.org.in.