Engineering Method to Estimate the Blade Loading of Propellers in Nonuniform Flow

Abstract

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Numerical Investigation of Propeller–Flap Interaction in Inclined Over-the-Wing Distributed-Propulsion Systems

“…Hence, the numerical model captures the performance of the installed propeller measurement more accurately, due to less flow separation on the blades. The onset of blade stall at these high-thrust conditions also implies that the thrust coefficient varies only slightly with advance ratio, which explains why the differences in thrust between the installed and uninstalled cases are relatively small (Δ = 0.005) when compared to the reductions in propeller thrust that are typically obtained in over-the-wing configurations [14,19,26]. The computed lift-coefficient in the uninstalled case compares reasonably well with the measured one.…”

“…In order to gain further confidence in the numerical setup, the results of the isolated wing, propeller, and installed baseline configuration are compared with experimental results obtained in Refs. [24,26]. In particular, the capability of the unsteady RANS simulations to capture propeller-induced flow separation on the flap will be assessed.…”

“…The thrust coefficients predicted by the CFD simulations show an acceptable agreement with the values obtained in the experiment, showing a difference of Δ = −0.017 (4.8%) and Δ = −0.007 (2.0%) in the uninstalled and installed cases, respectively. The discrepancy is larger in the uninstalled case because the propeller is operating in the non-linear region (low advance ratio) of the thrust curve [26], at which a larger portion of the blades have stalled in the isolated configuration than in the installed configuration. Hence, the numerical model captures the performance of the installed propeller measurement more accurately, due to less flow separation on the blades.…”

“…The detailed geometry of a propeller blade, including the chord and blade pitch-angle distribution, can be found in Ref. [26].…”

Aerodynamic Performance of Wingtip-Mounted Propellers in Tractor and Pusher Configuration

“…The selected propeller model featured a diameter of 0.2032 m and six unswept blades, and is described in detail by van Arnhem et al [14] This propeller was selected because its design is representative of propellers used on regional aircraft in terms of disk loading and blade loading. The blade pitch angle of the propeller could be adjusted manually.…”