Development Of Analytic Aerodynamic Model For Subsonic Blended-Wing-Body Under Mdo Environment

To develop fast and reliable aerodynamic analysis and design ability for Blended-Wing-Body aircraft at conceptual design stage, an analytical aerodynamic model different from conceptual formula or CFD is presented. It bases on intermediate fidelity analysis, with three components including basic aerodynamic model, longitudinal trim model and inverse design module. The basic aerodynamic model could evaluate performance at subsonic; the longitudinal trim model deals with the trim and control allocation of Blended-Wing-Body aircraft which often has several control surfaces distributed along the span of wing; and the inverse module provides a redesign ability for span wise lift distribution. Through three design practices including aerodynamic optimization for a 300-seat transport, cruise and approach longitudinal trim analysis for a UAV with 4 control surfaces, and redesign of span load distribution of a UAV, the analytical aerodynamic model shows well application in aircraft conceptual design work, and this makes it very suitable for MIX) integration. Current work provides basis for further weight and performance analysis, and becomes a central part for MDO framework.