Aerodynamic design of multi-propeller/wing integration at low Reynolds numbers

Abstract Based on the detailed flow characteristics analyses of a base four-propeller/wing integration at a low Reynolds number of 3.0 × 10 5 , new multi-propeller/wing integrated aerodynamic design philosophy and methodology have been developed and validated numerically. The core of the present design philosophy is to make good use of coupling effects between two adjacent propellers to realize the low-Reynolds-number flow-field reconstruction, thus to improve the aerodynamic performance of the multi-propeller/wing integration at the operating power-on state. The multi-reference frame (MRF) technique which quasi-steadily solves the Reynolds-averaged Navier–Stokes (RANS) equations coupled with transition model is used to design the example four-propeller/wing integration at a low Reynolds number of 3.0 × 10 5 . As a result, the designed multi-propeller/wing integration yields a maximum lift-to-drag ratio of 72.81, which represents a 21.08% increase compared to the base four-propeller/wing integration.

[1]  Fernando Martini Catalano.  On the Effects of an Installed Propeller Slipstream on Wing Aerodynamic Characteristics , 2004 .

[2]  Brian J. German,et al.  Wing Aerodynamic Analysis Incorporating One-Way Interaction with Distributed Propellers , 2014 .

[3]  Nicholas K. Borer,et al.  Drag Reduction Through Distributed Electric Propulsion , 2014 .

[4]  Fumiyasu Makino,et al.  Propeller Slipstream Interference with Wing Aerodynamic Characteristics of Mars Airplane at Low Reynolds Number , 2014 .

[5]  Belur Raghavan Rakshith,et al.  Optimal Low-Drag Wing Planforms for Tractor-Configuration Propeller-Driven Aircraft , 2015 .

[6]  F. X. Caradonna,et al.  Experimental and Analytical Studies of a Model Helicopter Rotor in Hover , 1980 .

[7]  Ilan Kroo,et al.  Propeller^Wing Integration for Minimum Induced Loss , 1986 .

[8]  Colin P. Britcher,et al.  EXPERIMENTAL INVESTIGATION OF THE EFFECT OF PROPELLER SLIPSTREAM ON BOUNDARY LAYER BEHAVIOR AT LOW REYNOLDS NUMBER , 2000 .

[9]  R. M. Hicks,et al.  Wing Design by Numerical Optimization , 1977 .

[10]  Bruce J. Holmes,et al.  Wing laminar boundary layer in the presence of a propeller slipstream , 1988 .

[11]  Giulio Romeo,et al.  HELIPLAT: Aerodynamic and Structural Analysis of HAVE Solar Powered platform , 2002 .

[13]  Brian J. German,et al.  Conceptual Design of Electric Aircraft with Distributed Propellers: Multidisciplinary Analysis Needs and Aerodynamic Modeling Development , 2014 .

[14]  Di-Bao Wang,et al.  CLASSIFICATION OF AIRFOILS BY ABNORMAL BEHAVIOR OF LIFT CURVES AT LOW REYNOLDS NUMBER , 2005 .

[15]  C. Britcher,et al.  Physical Model of a Propeller Slipstream Interacting with a Boundary Layer at Low Reynolds Number , 2004 .

[16]  Yong Zhao,et al.  Optimization design of satellite separation systems based on Multi-Island Genetic Algorithm , 2014 .

[17]  Leo L. Veldhuis,et al.  Aerodynamic optimisation of wings in multi-engined tractor propeller arrangements , 2000 .

[18]  R. Boucher,et al.  History of solar flight , 1984 .

[19]  Ralph J. Volino,et al.  A new model for free-stream turbulence effects on boundary layers , 1998 .

[20]  Li Jiang,et al.  Direct numerical simulation of flow separation around a NACA 0012 airfoil , 2005 .

[21]  L L M Veldhuis.  Optimization of Tractor Propeller/Wing Configurations , 1995 .

[22]  D. K. Walters,et al.  A Three-Equation Eddy-Viscosity Model for Reynolds-Averaged Navier-Stokes Simulations of Transitional Flow , 2008 .

[23]  Sally A. Viken,et al.  Computational Analysis of Powered Lift Augmentation for the LEAPTech Distributed Electric Propulsion Wing , 2017 .

[24]  Alex M. Stoll.  Comparison of CFD and Experimental Results of the LEAPTech Distributed Electric Propulsion Blown Wing , 2015 .

[25]  F. Hsiao,et al.  Experimental studies of airfoil performance and flow structures on alow Reynolds number airfoil , 1987 .

[26]  Piotr Doerffer,et al.  NUMERICAL SIMULATION OF MODEL HELICOPTER ROTOR IN HOVER , 2008 .