An oxide/oxide ceramic fiber-matrix composite (CMC) has been extensively characterized for high-temperature aerospace structural applications. This CMC is called GEN-IV(TM), and it has a porous and cracked aluminosilicate matrix reinforced by 3M Nextel 610(TM) alumina fibers woven in a balanced eight harness weave (8HSW). This CMC has been specifically designed without an interphase between the fiber and matrix, and it relies on the porous matrix for flaw tolerance. Stress-strain response is nearly linear to failure and without a well-defined proportional limit in tension and compression. In-plane shear and interlaminar strength increases with increasing temperature. The 1000degreesC fatigue limit in air at 105 cycles is 160 MPa, and the residual tensile strength of run-out specimens is not affected by the fatigue loading. The creep-rupture resistance above 1000degreesC is relatively poor, but it can be improved with a more-creep-resistant fiber.