better results with less energy symmetric airfoils 12% thickness zas

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