diff --git a/aerodynamic_analysis/src/methods/liftingLineForTAW.cpp b/aerodynamic_analysis/src/methods/liftingLineForTAW.cpp
index 24cf161be257236f5640b2ee253b64dabeb918b4..834def0d6e353efe0e51bec6fe1bd69801465a6f 100644
--- a/aerodynamic_analysis/src/methods/liftingLineForTAW.cpp
+++ b/aerodynamic_analysis/src/methods/liftingLineForTAW.cpp
@@ -811,7 +811,7 @@ double liftingLineForTAW::getFuselageCM0(const uint16_t& machID) {
     double deltaFuselage = -1.8 * (1. - 2.5 * geom2::measure::width_max(theFuselage) / geom2::measure::length(theFuselage))
                            * (PI * geom2::measure::width_max(theFuselage) * geom2::measure::height_max(theFuselage) * geom2::measure::length(theFuselage))
                            / (4. * geom2::measure::reference_area(liftingSurfaces.front()) * geom2::measure::mean_aerodynamic_chord(liftingSurfaces.front()))
-                           * (myLL_vec.at(machID).theLLOutputPt->CLatAoA0 / ( convertRadian(DEGREE, myLL_vec.at(machID).theLLOutputPt->dCLtodAoA_wf)));
+                           * (myLL_vec.at(machID).theLLOutputPt->CLatAoA0 / ( convertUnit(RADIAN, DEGREE, myLL_vec.at(machID).theLLOutputPt->dCLtodAoA_wf)));
     return deltaFuselage;
 }