High-Lift Aerodynamics

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

“…It is unclear what impact the diffused wakes have on global quantities of interest, because so many other factors also come into play. However, Smith 38 made the observation that when wakes and boundary layers merge too quickly, early separation will set in. This implies that under-resolution of the wakes in a CFD computation could influence stall prediction.…”

Application of Finite Volume Method in Fluid Dynamics and Inverse Design Based Optimization

“…The other three are in reasonable agreement and Stratford's method tended to predict separation slightly early. The Cebeci-Smith method is appeared to be best and the Head method is a strong second one (Smith, 1975). Due to the good accuracy, simple expressions and conservative characteristics for predicting separation, Stratford's method has been used in followings (Veress et al, 2011).…”

“…There are several existing methods for predicting separation as Goldschmied, Stratford, Head, and Cebeci-Smith for example (Smith, 1975). The accuracy these methods were examined several times.…”

Improved Representation of High-Lift Devices for a Multidisciplinary Conceptual Aircraft Design Process

“…Although the positive effects of slotted flaps have been known for almost a century [3], the underlying physics of the highly complex flows involved were not thoroughly understood until the 1970s, and much of the credit for changing this is given to Smith [4]. It was only after this point that analytical and numerical methods for the design of high-lift devices could be developed.…”

“…However, the computational costs of these methods are still relatively high because they require solution of the boundary-layer equations as well as algorithms for correlating the inviscid and the boundary-layer flow, all in addition to the inviscid flow solution itself. Although an accurate prediction of maximum obtainable lift is surely not possible without considering the boundary layer and flow separation, [4] shows that the principal effects of high-lift devices are due to flows induced by the airfoil elements on each other. It should therefore be possible to model the increments in lift, induced drag, and pitching moment for most of the flight envelope with potential theory alone.…”