This invention relates to composite materials and the production of composite materials that are designed for use under high stress and at high temperatures. More particularly, this invention relates to materials suited for use in turbine engines, such as those used in aircraft, that must withstand high temperature, high stress, corrosion and oxidation. The invention specifically relates to composite materials which have alloy matrices, e.g., nickel aluminide, reinforced with a substantially continuous, interpenetrating, and interconnected network of a metal oxide. These composite materials have superior properties as compared to superalloys, intermetallics, ceramics, or artificially reinforced materials.