This paper presents the use of a conventional computational-fluid-dynamics-based throughflow method to model the effects of a bypass fan in a propulsion system (for example, nacelle) under the restriction that information about the fan blade geometry is unavailable. Instead, the fan body-force model requires fan-performance data at different operating points as input. A simple implementation strategy is proposed to achieve this goal and extend the use of the body-force model to off-design operating conditions where fan-performance data are limited. This approach has been validated with axisymmetric calculations on three blade rows to demonstrate its capability at off-design conditions. The tool may be very useful to nacelle designers, who often have limited information about fan-performance data from engine suppliers.

本文介绍了使用传统的基于计算流体动力学的通流方法来建模推进系统（例如机舱）中的旁通风扇的效果，但前提是无法获得有关风扇叶片几何形状的信息。取而代之的是，风扇力模型需要输入不同运行点的风扇性能数据作为输入。提出了一种简单的实施策略来实现此目标，并将体力模型的使用扩展到风扇性能数据受限的非设计运行条件。该方法已经通过对三排叶片的轴对称计算进行了验证，以证明其在非设计条件下的能力。该工具对机舱设计人员可能非常有用，他们通常对来自发动机供应商的风扇性能数据了解有限。