1970 
flo 1, 2 
solution of 2D potential flow by conformal mapping 

syn 1 
solution of inverse problem by conformal mapping (Lighthill's
method) 
19713 
flo 6 
2D transonic potential flow (rotated difference scheme) 
1975 
flo 22 
first transonic potential flow solution for a swept wing (coauthor
D. Caughey)
first used for the wing design of the Canadair Challenger,
later marketed as XFLO 22 by the Dutch NLR, still in use today at
Boeing, Long Beach 
1977 
flo 27 
3D potential flow in general grid with trilinear isoparametric elements
(incorporated in Boeing A488 software) 
1979 
flo 36 
multigrid solution of 2D transonic potential flow in 310 (.06
sec. on IBM T30 laptop) 
1981 
flo 57 
solution of 3D Euler equations
 used worldwide; derivatives include NASA's TLNS3D, Lockheed's
TEAM code, British Aerospace's codes EJ30,
EJ65, Dornier Ikarus code 
1983 
flo 82 
multigrid solution of 2D Euler Equations in 2550 steps 
1985 
flo 67 
multigrid solution of 3D Euler equations in 2550 steps 
1985 
airplane 
first solution of Euler equations for a complete aircraft (tetrahedral
mesh) used by McDonnell Douglas (MD 11), NASA (HSCT), Mitsubishi, EADS (basis
of their current software Airplane+) 
1988 
flo 97, 107 
cellvertex and cellcentered schemes for 3D NavierStokes equations 
1989 
syn 36 
airfoil design in transonic potential flow via control theory 
1991 
uflo 82, 87 
dual timestepping scheme for unsteady flow
 used in Tflo code for Stanford's ASCI project 
19935 
syn 87, 88 
wing design by control theory using 3D Euler equations 
1997 
syn 107 
wing design by control theory using 3D NavierStokes equations 
2001 
flo 82sgs 
"textbook" multigrid solution of 2D and 3D Euler equations 

flo 88sgs 
35 steps with nonlinear symmetric GaussSeidel scheme 
2003 
synplane 
aerodynamic design of complete aircraft using control theory with tetrahedral
mesh 
2003 
flo3xx 
viscous flow solution on arbitrary polyhedral meshes 

syn3xx 
aerodynamic design of general configurations in viscous flow on arbitrary
meshes 