better results with less energy symmetric airfoils 12% thickness zas
Transcrição
better results with less energy symmetric airfoils 12% thickness zas
ZASWINGS FOR VENTRAL FINS AND FAIRINGS FIXED SURFACES WITHOUT FLAPS CD x CL AT REYNOLDS 1.6*10^6 AND MACH 0.08 BETTER RESULTS WITH LESS ENERGY STABILIZERS, FINS AND FAIRINGS SYMMETRIC AIRFOILS COMPARED TO NACA AIRFOILS ZASWINGS is a parameterized family of airfoils with thickness distribution based on QUARTIC equations 12% THICKNESS ZAS AIRFOIL COMPARED TO NACA0012, NACA0012-64, NACA16-012 NACA 16-012 AND ZAS-V08F00E4040T5050N5050ANY0012 CD x CL AT DIFFERENT REYNOLDS AND MACH NUMBERS ZASWINGS03.doc Página 1 de 10 - 5/3/2014 FLOW AT ALFA ZERO – NR 1.6*10^6 MACH 0.08 FLOW AT CL 0.20 – NR 1.2*10^6 MACH 0.06 NACA16-012 NACA16-012 AT CL=0.20 CD = 0.004 CD = 0.006 CD = 0.004 CD = 0.005 ZAS-V08F00E4040T5050N5050ANY0012 ZAS-V08F00E4040T5050N5050ANY0012 ZASWINGS03.doc Página 2 de 10 - 5/3/2014 WITH FLAPS FOR FLIGHT CONTROL CL x ALFA - 15 DEGREE PLAIN FLAPS AND NO FLAPS CD x CL - 05 DEGREE PLAIN FLAPS CD x CL - 15 DEGREE PLAIN FLAPS CM x ALFA - 15 DEGREE PLAIN FLAPS AND NO FLAPS ZASWINGS03.doc Página 3 de 10 - 5/3/2014 FLOW WITH FLAP 05 DEGREE NACA0012 CL=0.8 10% THICKNESS COMPARED TO NACA0010, NACA64A010 MACH 0.20 - NR 4.0 x 10^6 0.40 CHORD ELEVATOR - 10 DEGREE DEFLEXION HIGHER LIFT WITH FLAPS L/D = 77.91 HIGHER LIFT WITH NO FLAPS HIGHER L/D LOWER DRAG AT ZERO LIFT L/D=78.94 ZAS-V11F00E5555T4949N5050ANY0012 CL=0.8 ZASWINGS03.doc Página 4 de 10 - 5/3/2014 8% THICKNESS ZAS AIRFOIL COMPARED TO NACA64A008 FLOW COMPARED TO NACA0008-34, NACA64A008 MACH 0.20 - NR 4.0 x 10^6 NACA0008-34 CD=0.003 SEVERAL ZAS THICKNESS COMPARED TO NACA64A008 CD=0.003 ZAS-V08F00E4242T4949N5050ANY0008 ZASWINGS03.doc Página 5 de 10 - 5/3/2014 MACH 0.80 - NR 2.0 x 10^6 18% THICKNESS ZAS AIRFOIL NACA64A008 COMPARED TO NACA633018 FLOW AT CL 0.20 – NR 4.0*10^6 MACH 0.20 NACA633018 CD=0.006 CD=0.005 CD=0.004 ZAS-V10F00E5555T4949N5050ANY0008 CD=0.004 ZAS-V10F00E6060T4949N5050ANY0018 ZASWINGS03.doc Página 6 de 10 - 5/3/2014 ZAS - LOW DRAG HIGH LIFT PITCHING MOMENT TO LIFT 12% ZAS COMPARED TO NACA0012, NACA0012-64 MACH 0.08 e 0.20 - NR 1.6 e 4.0 x 10^6 CD x CL STABLE PITCHING VERY HIGH MAXIMUM CL HIGH EFFICIENCY VERY STEEP LIFT SLOPE HIGH EFFICIENCY CL x ALFA CL/CD TO CL ZASWINGS03.doc Página 7 de 10 - 5/3/2014 FLOW AT ALFA 8 DEGREES – NR 4.0*10^6 MACH 0.20 FLOW AT ALFA 14 DEGREES – NR 4.0*10^6 MACH 0.20 NACA0012 NACA0012 CL=0.904 L/D=100.51 CL=0.954 L/D=107.35 ZAS-V10F00E5555T4949N5050ANY0008 CL=1.532 L/D=87.37 CL=1.617 L/D=93.03 ZAS-V10F00E5555T4949N5050ANY0008 ZASWINGS03.doc Página 8 de 10 - 5/3/2014 FLOW AT CL = 1.10 – NR 4.0*10^6 MACH 0.20 ZAS - LOW DRAG LOW REYNOLDS NACA0012 ALFA=9.55 L/D=100.91 DRAG AT ZERO ALFA PITCHING MOMENT TO CL ALFA=9.28 L/D=111.93 ZAS-V15F00E8080T5050N6565ANY0012 ZASWINGS03.doc Página 9 de 10 - 5/3/2014 FLOW AT ALFA 0 DEGREES – NR 0.2*10^6 MACH 0.13 FLOW AT ALFA 0 DEGREES – NR 0.5*10^6 MACH 0.09 CD=0.010 CD=0.006 ZAS-V13F00E8585T5050N5050ANY0012 ZAS-V11F00E6565T5050N5050ANY0012 NACA0012 NACA0012 CD=0.009 CD=0.007 ZASWINGS03.doc Página 10 de 10 - 5/3/2014