This paper described the efforts to develop the inverse airfoil design methodology of the aspirated compressor

showing the potential to greatly increase compressor blade loading.The study began with a single stage aspirated compressor aero design based on the performance requirement of the front three stage of an advanced test HP compressor

in order to determine the high loading for following development of the airfoil inverse design methodology.Based on the method developed

the successful design for the rotor tip section of the single stage aspirated compressor is demonstrated.