boundaryconditions.m

计算气动力边界条件

function BoundaryConditions(h,N)
global rou T V;
%Subsonic inflow boundary(point 1) conditions
 rou(h,1)=1;
 V(h,1)=2*V(h,2)-V(h,3);
 T(h,1)=1;
%Supersonic outflow boundary(point N) conditions  
 V(h,N)=2*V(h,N-1)-V(h,N-2);
 rou(h,N)=2*rou(h,N-1)-rou(h,N-2);
 T(h,N)=2*T(h,N-1)-T(h,N-2);