Composite laminates are riveted to the metal frame when applied on aircrafts, hence the boundary condition of composite laminates is four-edge clamped. Based on the real application, the differences of quasi-static indentation damage of the composite laminates with the four edges clamped simply supported were systemically compared from four aspects: delamination propagation mode, contact force, dent depth and damage width. The experimental results show that all these four aspects are different when composite laminates are loaded under different boundary conditions. Also the results can provide experimental data for investigating the quasi-static indentation damage of composite laminates on the basis of real application.