When the wing area required to perform a given mission is determined by takeoff and/or landing yerformance, wing area can be reduced through the application of Leading Edge Blowing Boundary Layer Control (L.E. BLC). The aerodynamic development of a high pressure BLC nozzle composed of a row of small drilled holes is presented and the results are shown to compare favorably to the performance of a more conventional continuous-slot nozzle. A wind tunnel technique (originally developed by the French at O.N.E.R.A.) of modelling only the leading edge portion of a high-lift airfoil was utilized to evaluate small , yet critical, nozzle details on a large (40 % full-scale) size. (DePo)
Aerodynamic development of a high pressure leading edge blowing boundary layer control system
Entwicklung eines aerodynamischen Systems fuer die Kontrolle der Grenzschichtstroemungen auf der vorderen Fluegelklappe
AIAA-Papers ; Jan ; 1-7
1979
7 Seiten, 22 Bilder, 9 Quellen
Aufsatz (Konferenz)
Englisch
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