Evaluation of propulsor aerodynamic performance for powered aircraft wind tunnel experiments
Author(s)Siu, Nina M
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.
Edward M. Greitzer and Alejandra Uranga.
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This thesis describes a methodology to convert electrical power measurements to propulsor mechanical ow power for a 1:11-scale, powered wind tunnel model of an advanced civil aircraft utilizing boundary layer ingestion (BLI); mechanical ow power is a surrogate for aircraft fuel burn. Back-to-back experiments of BLI and non-BLI aircraft configurations to assess the BLI benet directly measured electrical power, and supporting experiments were performed in a 1x1 foot wind tunnel at the MIT Gas Turbine Laboratory to convert these measurements into mechanical flow power. The incoming flow conditions of the powered wind tunnel tests (Reynolds number and inlet distortion) were replicated. This propulsor characterization was found to convert the electrical power measurements to mechanical ow power with experimental uncertainty of roughly 1.6%.
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.Cataloged from student-submitted PDF version of thesis.Includes bibliographical references (pages 91-92).
DepartmentMassachusetts Institute of Technology. Department of Aeronautics and Astronautics.
Massachusetts Institute of Technology
Aeronautics and Astronautics.