A fixture for testing one or more axial loads in a flexible aerodynamic member , the fixture comprising: a structural frame assembly having a first end portion , a second end portion , and an intermediate portion between the first end portion and the second end portion ; a first pivotal linkage assembly attached to the first end portion , the first pivotable linkage assembly pivotable about a pitch axis and coupled to an axial reaction member ; a pair of pitch actuators operably coupled to the first pivotal linkage assembly , to apply a pitch moment to the first pivotal linkage assembly ; a second pivotal linkage assembly attached to the first pivotal linkage assembly , the second pivotal linkage assembly pivotable about a flap axis , the flap axis being perpendicular to the pitch axis , and the second pivotal linkage assembly having a first holding apparatus that is configured to hold an inboard end portion of the flexible aerodynamic member ; a pair of flap actuators operably coupled to the second pivotal linkage assembly , to apply a flap bending moment to the second pivotal linkage assembly ; a third pivotal linkage assembly attached to the second end portion of the structural frame assembly , the third pivotal linkage assembly pivotable about the pitch axis , and having a second holding apparatus that is configured to hold an outboard end portion of the flexible aerodynamic member ; and a pair of chord actuators operably coupled to the third pivotal linkage assembly to apply axial load to the flexible aerodynamic member , via the third pivotal linkage assembly , thereby minimizing deflections of the outboard end portion of the flexible aerodynamic member during testing of the one or more axial loads in the flexible aerodynamic member . a structural frame assembly having a first end portion , a second end portion , and an intermediate portion between the first end portion and the second end portion ; a first pivotal linkage assembly attached to the first end portion , the first pivotable linkage assembly pivotable about a pitch axis and coupled to an axial reaction member ; a pair of pitch actuators operably coupled to the first pivotal linkage assembly , to apply a pitch moment to the first pivotal linkage assembly ; a second pivotal linkage assembly attached to the first pivotal linkage assembly , the second pivotal linkage assembly pivotable about a flap axis , the flap axis being perpendicular to the pitch axis , and the second pivotal linkage assembly having a first holding apparatus that is configured to hold an inboard end portion of the flexible aerodynamic member ; a pair of flap actuators operably coupled to the second pivotal linkage assembly , to apply a flap bending moment to the second pivotal linkage assembly ; a third pivotal linkage assembly attached to the second end portion of the structural frame assembly , the third pivotal linkage assembly pivotable about the pitch axis , and having a second holding apparatus that is configured to hold an outboard end portion of the flexible aerodynamic member ; and a pair of chord actuators operably coupled to the third pivotal linkage assembly to apply axial load to the flexible aerodynamic member , via the third pivotal linkage assembly , thereby minimizing deflections of the outboard end portion of the flexible aerodynamic member during testing of the one or more axial loads in the flexible aerodynamic member . <EOS>