In the search for methods of reducing aircraft drag, the engine nacelle is considered as a candidate for laminar flow control. Preliminary results from wind tunnel tests on a two dimensional model of Laminar Flow Control (LFC) by suction nacelles, are presented. An approach to transition prediction using stability theory is outlined. The experimental results demonstrated the achievement of laminar flow by suction to a length Reynolds number of 4,600,000, in a two dimensional model with a pressure distribution similar to that found on a conventional aero engine nacelle. The theoretical results obtained to date are not inconsistent with the experimental results. The theoretically predicted separation bubble is located above the first suction compartment of the laminar flow central model and would be removed with the application of suction.
Application of Laminar Flow to AERO Engine Nacelles
1991
9 pages
Report
Keine Angabe
Englisch
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