Numerical Analysis of Aerospike Engine Nozzle Performance at Various Truncation Lengths

The aerospike engine was first devised in the early 1960s where it provided new means of reaching orbit a single stage. paper aimes to demonstrate viability technology by showcasing increased nozzle thrust efficiency over conventional bell nozzle. Various truncations were applied and each subjected two conditions, an over-expansion near optimum condition. contour developed using simple approximation method chosen replicate that XRS-2200. This anchored data, thereby validating computational fluid dynamics (CFD) simulation. Simulations completed for at pressure ratios (NPR) 58 15. Velocity vector plots contours generated which recirculation region can be clearly identified. is result negative contribution base grows increasingly when truncation increases addition exhaust flow over-expanded. results performance gain full-length nozzle, , all other truncations. At NPRs 15 showed 1.5% 10.3% respectively compared . There are, many impracticalities related including cooling on Therefore, provide realistic would implemented. Although radical design changes rocket will required adaptation engines, beneficial long term. By increasing nozzles, less fuel per launch. Furthermore, removing multi-stage currently used, overall, have reliability due its reduced complexity.