NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-012A AIRFOIL (n64012a-il) Reynolds number: 500,000 Max Cl/Cd: 52.09 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64012a-il-500000-n5.txt Download as CSV file: xf-n64012a-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0000 0.08866 0.08581 -0.0089 1.0000 0.0093
-15.250 -1.0293 0.07851 0.07547 -0.0152 1.0000 0.0093
-15.000 -1.0523 0.07055 0.06732 -0.0199 1.0000 0.0093
-14.750 -1.0712 0.06400 0.06057 -0.0233 1.0000 0.0093
-14.500 -1.0856 0.05853 0.05491 -0.0258 1.0000 0.0094
-14.250 -1.0969 0.05387 0.05005 -0.0276 1.0000 0.0094
-14.000 -1.1121 0.04901 0.04498 -0.0288 1.0000 0.0095
-13.750 -1.1211 0.04521 0.04101 -0.0294 1.0000 0.0096
-13.500 -1.1243 0.04227 0.03793 -0.0294 1.0000 0.0098
-13.250 -1.1236 0.03990 0.03545 -0.0292 1.0000 0.0099
-13.000 -1.1204 0.03793 0.03337 -0.0287 1.0000 0.0101
-12.750 -1.1157 0.03619 0.03152 -0.0280 1.0000 0.0102
-12.500 -1.1102 0.03455 0.02977 -0.0270 1.0000 0.0104
-12.250 -1.1040 0.03302 0.02811 -0.0258 1.0000 0.0106
-12.000 -1.0972 0.03153 0.02648 -0.0243 1.0000 0.0108
-11.750 -1.0892 0.03012 0.02493 -0.0227 1.0000 0.0110
-11.500 -1.0799 0.02879 0.02345 -0.0210 1.0000 0.0112
-11.250 -1.0692 0.02756 0.02207 -0.0193 1.0000 0.0114
-11.000 -1.0568 0.02639 0.02076 -0.0176 1.0000 0.0117
-10.750 -1.0420 0.02527 0.01950 -0.0163 1.0000 0.0119
-10.500 -1.0256 0.02429 0.01839 -0.0151 1.0000 0.0122
-10.250 -1.0078 0.02343 0.01741 -0.0140 1.0000 0.0125
-10.000 -0.9890 0.02267 0.01654 -0.0131 1.0000 0.0127
-9.750 -0.9741 0.02131 0.01507 -0.0116 1.0000 0.0131
-9.500 -0.9564 0.02040 0.01410 -0.0104 1.0000 0.0134
-9.250 -0.9375 0.01964 0.01328 -0.0094 1.0000 0.0137
-9.000 -0.9181 0.01895 0.01254 -0.0083 1.0000 0.0140
-8.750 -0.8985 0.01829 0.01183 -0.0073 1.0000 0.0143
-8.500 -0.8789 0.01766 0.01114 -0.0061 1.0000 0.0147
-8.250 -0.8594 0.01707 0.01049 -0.0050 1.0000 0.0151
-8.000 -0.8400 0.01654 0.00991 -0.0037 1.0000 0.0156
-7.750 -0.8210 0.01604 0.00936 -0.0023 1.0000 0.0161
-7.500 -0.7996 0.01553 0.00879 -0.0015 0.9986 0.0165
-7.250 -0.7692 0.01484 0.00805 -0.0026 0.9923 0.0171
-7.000 -0.7388 0.01418 0.00735 -0.0037 0.9848 0.0180
-6.750 -0.7083 0.01369 0.00683 -0.0047 0.9760 0.0190
-6.500 -0.6777 0.01325 0.00636 -0.0057 0.9659 0.0201
-6.250 -0.6474 0.01285 0.00590 -0.0065 0.9545 0.0214
-6.000 -0.6184 0.01244 0.00544 -0.0070 0.9415 0.0231
-5.750 -0.5912 0.01207 0.00506 -0.0071 0.9266 0.0258
-5.500 -0.5650 0.01180 0.00473 -0.0069 0.9112 0.0288
-5.250 -0.5402 0.01148 0.00438 -0.0064 0.8956 0.0339
-5.000 -0.5150 0.01123 0.00409 -0.0060 0.8809 0.0395
-4.750 -0.4899 0.01098 0.00381 -0.0055 0.8670 0.0479
-4.500 -0.4649 0.01071 0.00354 -0.0051 0.8538 0.0605
-4.250 -0.4402 0.01040 0.00327 -0.0046 0.8415 0.0825
-4.000 -0.4162 0.00996 0.00298 -0.0042 0.8295 0.1252
-3.750 -0.3934 0.00936 0.00266 -0.0036 0.8183 0.1996
-3.250 -0.3504 0.00793 0.00202 -0.0020 0.7979 0.4120
-3.000 -0.3260 0.00760 0.00189 -0.0015 0.7881 0.4797
-2.750 -0.3004 0.00742 0.00180 -0.0011 0.7790 0.5198
-2.500 -0.2741 0.00729 0.00172 -0.0008 0.7701 0.5503
-2.250 -0.2479 0.00717 0.00167 -0.0005 0.7618 0.5829
-2.000 -0.2217 0.00707 0.00164 -0.0002 0.7530 0.6124
-1.500 -0.1672 0.00700 0.00156 0.0001 0.7364 0.6437
-1.250 -0.1395 0.00696 0.00153 0.0001 0.7285 0.6534
-1.000 -0.1117 0.00696 0.00148 0.0001 0.7210 0.6610
-0.750 -0.0837 0.00693 0.00146 0.0001 0.7130 0.6680
-0.250 -0.0279 0.00692 0.00143 0.0000 0.6973 0.6828
0.000 0.0000 0.00694 0.00142 0.0000 0.6903 0.6903
0.250 0.0280 0.00692 0.00143 0.0000 0.6828 0.6973
0.750 0.0838 0.00693 0.00146 -0.0001 0.6679 0.7129
1.000 0.1117 0.00696 0.00148 -0.0001 0.6610 0.7210
1.250 0.1396 0.00696 0.00153 -0.0001 0.6534 0.7285
1.500 0.1673 0.00700 0.00156 -0.0001 0.6437 0.7364
2.000 0.2217 0.00707 0.00164 0.0002 0.6124 0.7531
2.250 0.2479 0.00717 0.00167 0.0005 0.5828 0.7618
2.500 0.2741 0.00729 0.00172 0.0008 0.5504 0.7701
2.750 0.3005 0.00742 0.00180 0.0011 0.5199 0.7790
3.000 0.3261 0.00760 0.00189 0.0015 0.4796 0.7881
3.250 0.3504 0.00793 0.00202 0.0020 0.4117 0.7978
3.500 0.3719 0.00862 0.00230 0.0028 0.3036 0.8080
3.750 0.3935 0.00936 0.00266 0.0036 0.1998 0.8183
4.000 0.4162 0.00996 0.00298 0.0042 0.1251 0.8295
4.250 0.4402 0.01040 0.00327 0.0046 0.0822 0.8415
4.500 0.4649 0.01071 0.00354 0.0051 0.0604 0.8538
4.750 0.4900 0.01098 0.00381 0.0055 0.0479 0.8669
5.000 0.5151 0.01123 0.00409 0.0060 0.0395 0.8808
5.250 0.5402 0.01148 0.00438 0.0064 0.0339 0.8957
5.500 0.5651 0.01180 0.00473 0.0069 0.0288 0.9113
5.750 0.5913 0.01207 0.00506 0.0071 0.0259 0.9266
6.000 0.6184 0.01244 0.00544 0.0070 0.0231 0.9414
6.250 0.6474 0.01285 0.00590 0.0065 0.0214 0.9545
6.500 0.6778 0.01325 0.00636 0.0057 0.0201 0.9659
6.750 0.7084 0.01369 0.00683 0.0047 0.0190 0.9760
7.000 0.7387 0.01418 0.00735 0.0037 0.0180 0.9849
7.250 0.7692 0.01484 0.00805 0.0026 0.0171 0.9922
7.750 0.8210 0.01604 0.00936 0.0023 0.0161 1.0000
8.000 0.8400 0.01654 0.00991 0.0037 0.0156 1.0000
8.250 0.8594 0.01707 0.01049 0.0050 0.0151 1.0000
8.500 0.8789 0.01766 0.01114 0.0061 0.0147 1.0000
8.750 0.8985 0.01829 0.01183 0.0073 0.0143 1.0000
9.000 0.9181 0.01894 0.01253 0.0083 0.0140 1.0000
9.250 0.9375 0.01964 0.01328 0.0094 0.0137 1.0000
9.500 0.9564 0.02040 0.01410 0.0104 0.0134 1.0000
9.750 0.9741 0.02131 0.01507 0.0116 0.0131 1.0000
10.000 0.9890 0.02267 0.01653 0.0131 0.0127 1.0000
10.250 1.0078 0.02343 0.01741 0.0140 0.0125 1.0000
10.500 1.0256 0.02428 0.01838 0.0151 0.0122 1.0000
10.750 1.0421 0.02527 0.01950 0.0163 0.0119 1.0000
11.000 1.0569 0.02639 0.02076 0.0176 0.0117 1.0000
11.250 1.0693 0.02755 0.02207 0.0192 0.0114 1.0000
11.500 1.0801 0.02879 0.02345 0.0210 0.0112 1.0000
11.750 1.0894 0.03011 0.02493 0.0227 0.0110 1.0000
12.000 1.0975 0.03152 0.02648 0.0243 0.0108 1.0000
12.250 1.1045 0.03301 0.02810 0.0257 0.0106 1.0000
12.500 1.1107 0.03454 0.02976 0.0269 0.0104 1.0000
12.750 1.1163 0.03617 0.03150 0.0279 0.0102 1.0000
13.000 1.1210 0.03791 0.03335 0.0286 0.0101 1.0000
13.250 1.1243 0.03989 0.03544 0.0291 0.0099 1.0000
13.500 1.1252 0.04224 0.03790 0.0293 0.0098 1.0000
13.750 1.1219 0.04519 0.04099 0.0292 0.0096 1.0000
14.000 1.1129 0.04901 0.04499 0.0287 0.0095 1.0000
14.250 1.0976 0.05389 0.05008 0.0274 0.0094 1.0000
14.500 1.0870 0.05848 0.05486 0.0257 0.0093 1.0000
14.750 1.0722 0.06401 0.06059 0.0231 0.0093 1.0000
15.000 1.0535 0.07056 0.06733 0.0196 0.0093 1.0000
15.250 1.0303 0.07857 0.07554 0.0149 0.0093 1.0000
15.500 1.0012 0.08871 0.08587 0.0086 0.0093 1.0000
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