This study depicts on algorithm for creating National Advisory Committee for Aeronautics (NACA) series wings based on the air foil’s governing equations. It is to assess their aerodynamic properties based on algorithms. The lift-to-drag (L/D) ratio and coefficients of lift and drag are computed by computation. The capabilities and behaviour of these airfoils can be better understood by creating NACA series wings and examining their aerodynamic characteristics. The programme is a useful resource for academics, engineers, and aero enthusiasts who want to learn more about and improve NACA series wings for diverse aerodynamic field applications. To evaluate the overall aerodynamic effectiveness and performance of NACA airfoils, computational models and experimental testing are used to test and analyse variables like lift, drag, stall behaviour, pressure distribution, and flow patterns. The evaluation aids in optimization of wing design, enhancement of aircraft performance and deepens knowledge of the aerodynamic concepts behind NACA series wings
Computational Algorithm To Generate NACA Series Profile For Aircraft Wing Design
09.08.2024
271551 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Bibliography of NACA papers on rotating-wing Aircraft
NTRS | 1948
|TIBKAT | 1985
|TIBKAT | 1979
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