Computatian of flow over airfoils under high 1ift separated flow conditions

Singh, JP and Rangarajan, R and Ramaswamy, MA (1985) Computatian of flow over airfoils under high 1ift separated flow conditions. Technical Report. National Aeronautical Laboratory, Bangalore, India.

Full text available as:
[img] PDF
Restricted to Archive staff only

Download (16Mb)


    This report presents preliminary results obta1ned from the code developed by Carlson to predict the pressure distribution over airfoils under 1ncompressible high 1ift separated flow conditions. In this method full potential equation 1s solved in cartesian coordinates coupled with13; Nash-Macdonald boundary layer program for lncorporating the viscous effects. For the potential flow calculation, direct boundary condition of surface flow tangency is applied upto the separation point, inverse boundary condition of constant pressure correspnniting to the pressure at the point of separation is applied. If the flow separation is only on the upper surface, as it happens at high 1ift ccmditions, the Kutt-condition corresponds to equating the pressure at the T.E. on the lower surface to the pressure at the separation point on the upper surface.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Separated flow;H1gh lift flow;Computational aerodynamics
    Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
    Division/Department: Aerodynamics, Aerodynamics, Aerodynamics
    Depositing User: Poornima Narayana
    Date Deposited: 18 Aug 2006
    Last Modified: 24 May 2010 09:46

    Actions (login required)

    View Item