The paper presents results obtained at an industrial level with a three-dimensional boundary layer method, run jointly with a source singularity program. The principal objective is flow analysis around helicopter fuselages and drag reduction. Because of the lack of an adequate wake model, the work focuses on the prediction of separation lines, whose location greatly influences fuselage drag. Many comparisons between computed results and wind tunnel results are described. The method appears to be sufficiently reliable for a successful use by project engineers.
Analyse Theorique et Experimentale des Decollements sur Fuselages d'Helicopteres (Theoretical and Experimental Analysis of Helicopter Fuselage Separations)
1985
31 pages
Report
Keine Angabe
Englisch
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