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The current work present a simple model to integrate non-linear aerodynamic in conceptual design phase, before wind tunnel testing. A presentation of a simple pitch up maneuver based on three different aerodynamic models is simulated. The simulation indicates different behaviors depending on the aerodynamic model, and shows the importance of including unsteady aerodynamic.

Flow visualization and force and moment measurements were conducted on a number of delta wing planforms and realistic configurations in order to ascertain the existence of Reynolds number effects. The results show the effect of Reynolds number at high angles of attack is insignificant in comparison to other effects such as tunnel blockage and support interference for highly swept lifting surfaces with sharp leading edges. For realistic configurations however the situation is significantly more complicated because of the interaction of vortices shed from the forebody and multiple lifting surfaces. In such cases, it is important to consider such effects carefully when extrapolating to full-scale Reynolds numbers.

The design modern aircraft requires integration of multidisciplinary models for analysis in early design phase to increase the chances of a successful project. In this paper, a framework for distributed aircraft analysis in the conceptual design including several domains is presented. The framework is based on so-called Web service standards, allowing integration of distributed models for system simulation and optimization using standardized interfaces. The analysis is controlled by a so-called sequencer which manages the interaction between simulation modules and an XML-based design data repository. This repository includes all design data and an executable process description defining the sequence for execution of the modules. In the paper, the framework with underlying concepts is described. The approach is further illustrated using the design of an Unmanned Aerial Vehicle as an example.