Experimental Evaluation of BLI Propulsion: The Boundary Layer Ingesting Inlet/Distortion-Tolerant Fan Solution

Arend, David J

关键词: BOUNDARY LAYER INGESTION PROPULSION;    PROPULSOR;    INGESTION (ENGINES);    ENGINE INLETS;    WIND TUNNEL TESTS;    ENGINE AIRFRAME INTEGRATION;    TEST STANDS;    TURBOFANS;    BOUNDARY LAYERS;   

RP-ID  :  GRC-E-DAA-TN58528

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

NASA has successfully developed a new testbed configuration for experimentally evaluating embedded boundary layer ingesting aircraft propulsors in its 8'x6' Supersonic Wind Tunnel. This testbed meets the challenges of providing the necessary freestream flow Mach conditions and desired range and distribution of boundary layer thickness for embedded aircraft propulsion systems. The testbed consists of a 48ft long raised wind tunnel floor aircraft surface simulator and a boundary layer regulation system to produce propulsion-local aircraft aerodynamic flow fields. This durable special test equipment is designed to be installed in the wind tunnel's transonic test section and is capable of evaluating a wide range of subcritical and supercritical airframe-propulsion integration configurations for subsonic cruise aircraft. The wind tunnel and testbed are well suited for meeting the test requirements of these propulsors in the most cost efficient way and has been aerodynamically calibrated and proven through tests of a first-of-its-kind boundary layer ingesting propulsor.