Computational Analysis of a Boundary Layer Ingesting Tailcone Thruster Configuration Using the LAVA Curvilinear Solver

AMS Seminar Series

Speakers: Luis S. Fernandes, Science and Technology Corporation/NASA Ames Research Center
and David T. Chan, Configuration Aerodynamics Branch, NASA Langley Research Center
September 19, 2024

Presentation

Seminar Slide Deck (PDF-18.2MB)

Abstract

Boundary layer ingesting (BLI) propulsion systems are one of the many technologies currently under investigation within the aerospace community to meet NASA's Advanced Air Transport Technology project goal of a sustainable future in aviation. To that end, an experimental campaign was conducted in the National Transonic Facility (NTF) wind tunnel to study the propulsion-airframe integration effects of the Boundary Layer Ingesting Tailcone System installed in the aft portion of a 2.7% scale design of the NASA Common Research Model (CRM). This test was accompanied by a numerical simulation effort using the Launch, Ascent, and Vehicle Aerodynamics (LAVA) curvilinear solver to validate the applicability of current best-practice Reynolds-Averaged Navier-Stokes (RANS) models in accurately predicting the relevant flow physics in free-air. A total of 205 steady RANS simulations were performed using LAVA, covering the range of conditions present in the NTF test matrix. Flow conditions ranged from 5- to 15-million Reynolds number, Mach numbers of 0.75, 0.80 and 0.85, and angles of attack between -3 and 4 degrees. Four different mass-flow plugs were also tested to assess propulsor operating condition effects. Sensitivity to these flow conditions is analyzed in detail, especially in terms of the nacelle flow distortion which was the main subject of the study. Aerodynamic load coefficients, aft body boundary layer measurements and fuselage pressure tap results are also discussed, providing a wide range of validation results from this experimental campaign. This validation effort shows that current best-practices using RANS models within the LAVA curvilinear solver flow solver are well suited for predicting the inlet flow distortion characteristics of novel aircraft configurations employing BLI at the aft end of the fuselage. This talk will cover the combined experimental and numerical efforts that resulted from this BLI-focused investigation.

This work is supported by NASA’s Advanced Air Transport Technology (AATT) Project.

Biography

Luis S. Fernandes is a research scientist/engineer for Science and Technology Corporation working in the Computational Aerosciences Branch of the NASA Advanced Supercomputing Division at NASA Ames Research Center (ARC). Fernandes obtained his Master’s degree in aerospace engineering from Instituto Superior Técnico in 2019, and joined the Launch, Ascent, and Vehicle Aerodynamics (LAVA) group in June 2020, after devoting the previous year to two separate internship positions in the Aerothermodynamics and Aerosciences branches at NASA Ames Research Center. Since joining the LAVA group, Fernandes has been working on applications using the structured curvilinear solver, ranging from noise predictions for turbofan engine applications using scale-resolving simulations, to wind tunnel model simulations for various projects within NASA’s Advanced Air Transport Technology (AATT) project.

David Chan is a Research Aerospace Engineer and Assistant Branch Head in the Configuration Aerodynamics Branch (CAB) at the NASA Langley Research Center. Chan obtained his M.S. Degree in Aerospace Engineering from the George Washington University before joining CAB in 2007 as an experimentalist supporting various NASA programs and projects. He has been principal investigator of large wind tunnel test campaigns on various aircraft and launch vehicle configurations in his career, including those focused on high Reynolds number research at the National Transonic Facility. Chan currently serves as a Technical Lead within the NASA Advanced Air Transport Technology Project.