Numerical simulation of propulsive aerodynamic profiles

The problem of creating high-lift propulsive aerodynamic is considered. A method was developed for constructing an profile by solving the inverse aerodynamics. dependence lifting force this on volume air sucked from its upper surface and angle attack studied. under study basis well-known Griffin/Goldschmid with suction at critical point. Three profiles have been developed. first has a flat lower to obtain ground effect. second similar but slit nozzle near trailing edge. third non-flat bottom increased thickness. solution aerodynamics used construct within model ideal gas. pressure distribution part profile, construction height range angles are 0° 16°, as well degree rarefaction up 0.5 atm in gap through which taken were set. For profiles, ratio amount ejected This ranged 50 % 200 %. Numerical calculations performed each variant using Spalart-Allmaras turbulence models Transition Shear Stress Transport (SST) Langtry model. parameters adjusted according known reference data. Reynolds number 1.5·105–1.5·106. high lift coefficient Cy = 3–3.4 achieved when vacuum intake atm. depends almost linearly maximum values. greater flow slot nozzle, Significance practical application. large thickness create traction. These convenient use aircraft internal volumes, example, those running hydrogen fuel.