NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-012A AIRFOIL (n64012a-il) Reynolds number: 200,000 Max Cl/Cd: 39.88 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64012a-il-200000-n5.txt Download as CSV file: xf-n64012a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-012A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8238 0.08751 0.08362 -0.0158 1.0000 0.0168
-13.000 -0.8478 0.07892 0.07490 -0.0216 1.0000 0.0167
-12.750 -0.8710 0.07157 0.06738 -0.0261 1.0000 0.0166
-12.500 -0.8935 0.06519 0.06079 -0.0294 1.0000 0.0166
-12.250 -0.9145 0.05974 0.05509 -0.0314 1.0000 0.0166
-12.000 -0.9335 0.05512 0.05020 -0.0320 1.0000 0.0167
-11.750 -0.9500 0.05120 0.04602 -0.0315 1.0000 0.0168
-11.500 -0.9598 0.04801 0.04265 -0.0303 1.0000 0.0170
-11.250 -0.9637 0.04565 0.04014 -0.0286 1.0000 0.0173
-11.000 -0.9647 0.04367 0.03802 -0.0266 1.0000 0.0176
-10.750 -0.9628 0.04177 0.03595 -0.0245 1.0000 0.0179
-10.500 -0.9579 0.03967 0.03362 -0.0227 1.0000 0.0182
-10.250 -0.9508 0.03745 0.03112 -0.0210 1.0000 0.0185
-10.000 -0.9407 0.03535 0.02876 -0.0194 1.0000 0.0188
-9.750 -0.9280 0.03337 0.02654 -0.0179 1.0000 0.0192
-9.500 -0.9131 0.03152 0.02443 -0.0166 1.0000 0.0197
-9.250 -0.8964 0.02984 0.02252 -0.0154 1.0000 0.0203
-9.000 -0.8783 0.02846 0.02092 -0.0143 1.0000 0.0211
-8.750 -0.8591 0.02722 0.01946 -0.0133 1.0000 0.0218
-8.500 -0.8395 0.02576 0.01783 -0.0123 1.0000 0.0223
-8.250 -0.8205 0.02430 0.01630 -0.0113 1.0000 0.0229
-8.000 -0.8013 0.02321 0.01517 -0.0102 1.0000 0.0236
-7.750 -0.7823 0.02227 0.01418 -0.0091 1.0000 0.0243
-7.500 -0.7635 0.02138 0.01324 -0.0078 1.0000 0.0252
-7.250 -0.7453 0.02054 0.01233 -0.0064 1.0000 0.0262
-7.000 -0.7277 0.01977 0.01150 -0.0048 1.0000 0.0273
-6.750 -0.7100 0.01915 0.01080 -0.0032 1.0000 0.0286
-6.500 -0.6956 0.01832 0.00998 -0.0011 1.0000 0.0304
-6.250 -0.6800 0.01771 0.00936 0.0008 1.0000 0.0323
-6.000 -0.6591 0.01711 0.00870 0.0016 0.9978 0.0346
-5.750 -0.6258 0.01645 0.00796 0.0000 0.9907 0.0378
-5.500 -0.5931 0.01572 0.00724 -0.0017 0.9833 0.0440
-5.250 -0.5609 0.01512 0.00663 -0.0031 0.9747 0.0531
-5.000 -0.5301 0.01454 0.00608 -0.0042 0.9648 0.0679
-4.750 -0.5004 0.01388 0.00556 -0.0052 0.9545 0.0981
-4.500 -0.4731 0.01295 0.00501 -0.0059 0.9438 0.1734
-4.250 -0.4497 0.01173 0.00441 -0.0060 0.9323 0.3084
-4.000 -0.4294 0.01077 0.00412 -0.0051 0.9192 0.4586
-3.750 -0.4037 0.01047 0.00400 -0.0047 0.9074 0.5242
-3.500 -0.3770 0.01029 0.00389 -0.0043 0.8961 0.5655
-3.250 -0.3499 0.01018 0.00379 -0.0040 0.8853 0.5964
-3.000 -0.3241 0.01010 0.00376 -0.0033 0.8740 0.6290
-2.750 -0.2988 0.01007 0.00377 -0.0025 0.8628 0.6590
-2.500 -0.2723 0.01004 0.00370 -0.0020 0.8524 0.6764
-2.250 -0.2453 0.01000 0.00361 -0.0017 0.8424 0.6883
-2.000 -0.2183 0.00996 0.00353 -0.0014 0.8320 0.6972
-1.750 -0.1910 0.00992 0.00342 -0.0012 0.8225 0.7059
-1.500 -0.1637 0.00989 0.00334 -0.0010 0.8130 0.7128
-1.250 -0.1365 0.00986 0.00326 -0.0009 0.8034 0.7212
-1.000 -0.1091 0.00984 0.00321 -0.0006 0.7951 0.7283
-0.750 -0.0819 0.00982 0.00316 -0.0005 0.7857 0.7365
-0.500 -0.0546 0.00981 0.00313 -0.0003 0.7771 0.7439
-0.250 -0.0273 0.00980 0.00310 -0.0002 0.7685 0.7524
0.000 0.0000 0.00980 0.00311 0.0000 0.7603 0.7603
0.250 0.0273 0.00980 0.00310 0.0002 0.7524 0.7685
0.500 0.0546 0.00981 0.00313 0.0003 0.7439 0.7771
0.750 0.0819 0.00982 0.00316 0.0005 0.7364 0.7857
1.000 0.1092 0.00984 0.00321 0.0006 0.7283 0.7951
1.250 0.1365 0.00986 0.00326 0.0009 0.7212 0.8034
1.500 0.1637 0.00989 0.00334 0.0010 0.7128 0.8130
1.750 0.1910 0.00992 0.00342 0.0012 0.7059 0.8225
2.000 0.2183 0.00996 0.00353 0.0014 0.6972 0.8320
2.250 0.2453 0.01000 0.00361 0.0017 0.6883 0.8424
2.500 0.2723 0.01004 0.00370 0.0020 0.6764 0.8524
2.750 0.2988 0.01007 0.00377 0.0025 0.6590 0.8628
3.000 0.3241 0.01010 0.00376 0.0033 0.6290 0.8740
3.250 0.3499 0.01018 0.00379 0.0040 0.5963 0.8853
3.500 0.3770 0.01029 0.00389 0.0043 0.5655 0.8961
3.750 0.4037 0.01047 0.00400 0.0047 0.5241 0.9074
4.000 0.4295 0.01077 0.00412 0.0051 0.4588 0.9193
4.250 0.4497 0.01173 0.00441 0.0060 0.3085 0.9323
4.500 0.4731 0.01295 0.00501 0.0059 0.1736 0.9438
4.750 0.5004 0.01388 0.00556 0.0052 0.0981 0.9544
5.000 0.5301 0.01454 0.00608 0.0042 0.0679 0.9647
5.250 0.5609 0.01512 0.00663 0.0031 0.0531 0.9747
5.500 0.5930 0.01572 0.00724 0.0017 0.0440 0.9833
5.750 0.6258 0.01645 0.00796 0.0000 0.0379 0.9907
6.000 0.6590 0.01711 0.00870 -0.0016 0.0346 0.9978
6.250 0.6800 0.01771 0.00936 -0.0008 0.0323 1.0000
6.500 0.6956 0.01832 0.00997 0.0011 0.0304 1.0000
6.750 0.7100 0.01915 0.01080 0.0032 0.0286 1.0000
7.000 0.7277 0.01977 0.01150 0.0048 0.0273 1.0000
7.250 0.7453 0.02054 0.01233 0.0064 0.0262 1.0000
7.500 0.7635 0.02138 0.01324 0.0078 0.0252 1.0000
7.750 0.7823 0.02226 0.01418 0.0091 0.0243 1.0000
8.000 0.8014 0.02321 0.01517 0.0102 0.0236 1.0000
8.250 0.8205 0.02430 0.01630 0.0113 0.0229 1.0000
8.500 0.8396 0.02576 0.01783 0.0123 0.0223 1.0000
8.750 0.8592 0.02722 0.01946 0.0133 0.0218 1.0000
9.000 0.8784 0.02846 0.02091 0.0143 0.0211 1.0000
9.250 0.8965 0.02984 0.02252 0.0154 0.0203 1.0000
9.500 0.9132 0.03152 0.02443 0.0166 0.0197 1.0000
9.750 0.9281 0.03338 0.02654 0.0179 0.0192 1.0000
10.000 0.9408 0.03535 0.02877 0.0193 0.0188 1.0000
10.250 0.9510 0.03745 0.03113 0.0209 0.0185 1.0000
10.500 0.9582 0.03967 0.03362 0.0227 0.0182 1.0000
10.750 0.9632 0.04177 0.03594 0.0245 0.0179 1.0000
11.000 0.9650 0.04369 0.03803 0.0265 0.0176 1.0000
11.250 0.9642 0.04564 0.04013 0.0285 0.0173 1.0000
11.500 0.9603 0.04803 0.04266 0.0302 0.0170 1.0000
11.750 0.9504 0.05124 0.04606 0.0314 0.0168 1.0000
12.000 0.9340 0.05516 0.05024 0.0319 0.0167 1.0000
12.250 0.9148 0.05982 0.05518 0.0312 0.0166 1.0000
12.500 0.8937 0.06531 0.06092 0.0292 0.0166 1.0000
12.750 0.8714 0.07169 0.06750 0.0259 0.0166 1.0000
13.000 0.8478 0.07915 0.07514 0.0212 0.0167 1.0000
13.250 0.8241 0.08775 0.08387 0.0154 0.0168 1.0000
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