A fixture (10, 10a) for testing one or more axial loads in a flexible aerodynamic member, the fixture (10, 10a) 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.