Previous experimental research [1] has shown that the National Advisory Committee for Aeronautics (NACA) 8 - series airfoils have high critical and drag divergence mach numbers compared to NACA 6 - series airfoils. By varying the minimum pressure locations, new such type of airfoils can be obtained. The newly designed airfoils are meshed and analyzed computationally using compressible solver settings and k-€ turbulence model. The above mentioned airfoils are submerged in flow fields of various Mach numbers and angle of attacks. The force and moment coefficients such as Cl, Cd are monitored and graphs have been plotted between each of the above coefficients and Mach number. The results are interpreted both graphically and analytically, and it is found that the critical Mach number is 0.7277 and 0.7645 for NACA 846A110 and NACA 837A110 airfoils respectively and the drag divergence Mach number is 0.785 and 0.794 for NACA 846A110 and NACA 837A110 airfoils respectively.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Design and computational analysis of NACA 846A110 and NACA 837A110 airfoils


    Contributors:

    Published in:

    Publication date :

    2011-03-01


    Size :

    1481473 byte





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Aerodynamic Characteristics of NACA 16-Series Airfoils

    Maksymiuk, C. M. / Watson Viken, S. A. | NTRS | 1986


    Chordwise Actuation Effects on NACA 0012 Morphing Airfoils

    Rocha dos Santos, Artur G. / Caselato de Sousa, Guilherme L. / Sanches, Augusto C. et al. | AIAA | 2018


    Generation and conformal mapping of the NACA airfoils

    Prosnak, Włodzimierz J. | TIBKAT | 1991