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Resistance capability of composite rectangular plates composed of CFRP, GFRP and their Hybrid were surveyed to investigate their applicability to UHB Propeller blades. Intralamina hybrid of CFRP and GFRP specimen was found promising. Impact testing on the rectangular and flat blade composite specimen supported in cantilever with projectiles made of Teflon was performed to determine the relative resistance performance and also to obtain the time history of strain on the specimens. Without assuming the time history of load, impact analyses using DYNA3D, a FEM program, were made at the same condition as the experiments to investigate the applicability of the impact analysis to simulate impact testing. The comparison of the analysis and the experiment was reasonably good and the applicability of the analysis method to predict responses of composite blades to impact was promised.

Applicability of a numerical code to aerodynamic design of a Prop-Fan is established by precise agreement of numerical results with experimental data, i.e., not only measured integrated performance indices, such as power coefficient or net efficiency but also pressure distribution on the blade surface should agree well with computed results. For this purpose, an Euler Code using the Total Variation Diminishing scheme has been developed. Numerical calculations are performed with this scheme for the SR-7L Prop-Fan at the freestream Mach number 0.5 and 0.78. The computed power coefficient, CP = 1.46 at M∞ = 0.5 shows good agreement with experimental data. At this computed CP, the computed pressure distributions on the blade surfaces show good agreement with the experimental results. For the 0.78M∞ case the computed CP of 0.87 also shows good agreement with the experimental results and the computed pressure distributions are in general agreement with the experimental data.