This thesis will present the development of a quasi-one-dimensional, viscous-inviscid
approach to assess the aerodynamic performance of low-speed wind tunnels and its application
to the preliminary design of a new wind tunnel. The approach includes numerical integration of
the incompressible, quasi-one-dimensional equations of motion coupled with the axisymmetric
integral boundary layer equations. The boundary layer model describes the viscous losses
necessary for predicting required fan input power. Components such as screens and fans are
modeled with discrete changes in the flow variables at specified locations. The approach can be
used to assess the aerodynamic performance of a given wind tunnel design to determine the
required fan input to overcome viscous losses from the boundary layer and components. Results
are provided for the conceptual design of a low-speed wind tunnel for testing turbomachinery.
For a fan diameter of 24 inches, a diffuser area ratio of 1.06 provides the maximum test
Reynolds number for a 300-horsepower constraint. The results show the utility of the approach
for preliminary aerodynamic analysis and design of low-speed wind tunnel designs, enabling
rapid design iterations for new wind tunnel designs and assessment of potential design
improvements for existing wind tunnels.
