[mlooti]

Hi every body

Im trying to get familiar with adjoint optimization in SU2

so after doing almost all of the tutorials and test cases I start to do an optimization on F16 fighter jet. I make the mesh in ANSYS meshing and then convert it to su2 format.
then I solved the configuration with euler equation. the solution converged and results seems good compared to fluent. just one thin

my problem is that the lift coefficient is negative???
I know that the orientation of the plain is ok but I dont know why the lift coeff is always negative (since I can not solve the adjoint equation based on my flow results with negative lift coeff.)

bellow is some part of the config file which I think is responsible for the prroblem

% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.9
%
% Angle of attack (degrees)
AoA= 0.0
%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.00
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional moment
REF_LENGTH_MOMENT= 1.0
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 6.807157e-7
%
%
% Reference element length for computing the slope limiter epsilon
REF_ELEM_LENGTH= 0.02
% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_ONE
%
%

thanks for helping