Published Paper Details:

Re-entry vehicles with double delta wing configuration are becoming an important topic of study in recent times due to the interest of many countries in space endeavor. Many studies are being performed with double-delta wings having different strake and wing swept angles with modification in wing profiles. In the present study, a reentry vehicle having a reflex aerofoil at the bottom and two different NACA symmetrical aerofoils at the top surface of the wing are examined in detail by solving the Euler's equations using explicit first order upwind scheme for a free stream Mach number two. The angle attack of the vehicle is varied from 100 to 500 in steps of 5. The coefficients of pressure, Mach number, density gradient at different span wise locations, and the overall lift and drag coefficients are used for characterizing the vehicles wing platform for the descent phase at an altitude of 60000ft. It has been observed that the variation of lift coefficient in both NACA0012 and NACA0020 is negligible up to 350 and it has increased to 18.48% in NACA0020 compared NACA0012 as the angle of attack increases. However, the NACA0020 aerofoil has shown an increase in drag coefficient from 2.57% to 18.43% compared to NACA0012 depending on the angle of attack. It suggests that NACA0020 could be used if more storage space is desired inside the wing as the variation in drag coefficient is within the limit.