NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63012A AIRFOIL (n63012a-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.57 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63012a-il-1000000-n5.txt Download as CSV file: xf-n63012a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63012A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0335 0.13926 0.13722 0.0225 1.0000 0.0068
-18.000 -1.1168 0.11241 0.11007 0.0084 1.0000 0.0067
-17.750 -1.1567 0.10012 0.09761 0.0019 1.0000 0.0066
-17.500 -1.1884 0.08977 0.08708 -0.0038 1.0000 0.0066
-17.250 -1.2125 0.08135 0.07851 -0.0083 1.0000 0.0066
-17.000 -1.2328 0.07392 0.07093 -0.0123 1.0000 0.0066
-16.750 -1.2476 0.06777 0.06464 -0.0154 1.0000 0.0067
-16.500 -1.2596 0.06239 0.05912 -0.0180 1.0000 0.0067
-16.250 -1.2688 0.05766 0.05427 -0.0201 1.0000 0.0067
-16.000 -1.2828 0.05254 0.04899 -0.0220 1.0000 0.0068
-15.750 -1.2940 0.04802 0.04433 -0.0235 1.0000 0.0068
-15.500 -1.3010 0.04422 0.04040 -0.0244 1.0000 0.0069
-15.250 -1.3038 0.04106 0.03713 -0.0250 1.0000 0.0070
-15.000 -1.3040 0.03835 0.03430 -0.0252 1.0000 0.0071
-14.750 -1.3011 0.03605 0.03191 -0.0252 1.0000 0.0072
-14.500 -1.2964 0.03404 0.02980 -0.0250 1.0000 0.0073
-14.250 -1.2900 0.03227 0.02794 -0.0246 1.0000 0.0074
-14.000 -1.2826 0.03066 0.02625 -0.0240 1.0000 0.0075
-13.750 -1.2741 0.02923 0.02473 -0.0232 1.0000 0.0076
-13.500 -1.2649 0.02791 0.02333 -0.0223 1.0000 0.0077
-13.250 -1.2550 0.02672 0.02205 -0.0212 1.0000 0.0079
-13.000 -1.2444 0.02562 0.02087 -0.0200 1.0000 0.0080
-12.750 -1.2330 0.02461 0.01978 -0.0186 1.0000 0.0081
-12.500 -1.2209 0.02369 0.01877 -0.0171 1.0000 0.0083
-12.250 -1.2076 0.02288 0.01787 -0.0156 1.0000 0.0084
-12.000 -1.1930 0.02214 0.01706 -0.0141 1.0000 0.0086
-11.750 -1.1763 0.02145 0.01630 -0.0129 1.0000 0.0088
-11.500 -1.1582 0.02078 0.01556 -0.0119 1.0000 0.0090
-11.250 -1.1394 0.02013 0.01483 -0.0110 1.0000 0.0091
-11.000 -1.1201 0.01949 0.01413 -0.0101 1.0000 0.0092
-10.750 -1.1002 0.01888 0.01345 -0.0092 1.0000 0.0092
-10.500 -1.0836 0.01793 0.01241 -0.0079 1.0000 0.0095
-10.250 -1.0648 0.01716 0.01158 -0.0069 1.0000 0.0097
-10.000 -1.0445 0.01654 0.01091 -0.0060 1.0000 0.0100
-9.750 -1.0232 0.01600 0.01033 -0.0052 1.0000 0.0102
-9.500 -1.0015 0.01553 0.00983 -0.0044 1.0000 0.0105
-9.250 -0.9795 0.01508 0.00934 -0.0037 1.0000 0.0108
-9.000 -0.9578 0.01463 0.00886 -0.0028 1.0000 0.0110
-8.750 -0.9364 0.01419 0.00838 -0.0019 1.0000 0.0112
-8.500 -0.9152 0.01377 0.00792 -0.0009 1.0000 0.0115
-8.250 -0.8876 0.01333 0.00745 -0.0013 0.9966 0.0117
-8.000 -0.8570 0.01291 0.00697 -0.0023 0.9903 0.0120
-7.750 -0.8258 0.01251 0.00654 -0.0034 0.9829 0.0123
-7.500 -0.7948 0.01210 0.00609 -0.0044 0.9733 0.0127
-7.250 -0.7650 0.01168 0.00565 -0.0051 0.9605 0.0135
-7.000 -0.7372 0.01136 0.00528 -0.0053 0.9435 0.0142
-6.750 -0.7116 0.01109 0.00496 -0.0050 0.9241 0.0149
-6.500 -0.6868 0.01087 0.00466 -0.0045 0.9041 0.0157
-6.250 -0.6617 0.01067 0.00438 -0.0040 0.8856 0.0164
-6.000 -0.6366 0.01042 0.00408 -0.0035 0.8679 0.0185
-5.750 -0.6109 0.01023 0.00384 -0.0032 0.8517 0.0207
-5.500 -0.5851 0.01002 0.00359 -0.0029 0.8370 0.0240
-5.250 -0.5590 0.00984 0.00337 -0.0027 0.8235 0.0277
-4.750 -0.5064 0.00945 0.00294 -0.0023 0.7992 0.0400
-4.500 -0.4799 0.00924 0.00274 -0.0021 0.7887 0.0504
-4.250 -0.4537 0.00901 0.00254 -0.0020 0.7786 0.0657
-4.000 -0.4274 0.00876 0.00235 -0.0018 0.7688 0.0869
-3.750 -0.4014 0.00847 0.00215 -0.0016 0.7599 0.1173
-3.500 -0.3763 0.00807 0.00194 -0.0013 0.7508 0.1695
-3.250 -0.3514 0.00762 0.00171 -0.0011 0.7423 0.2333
-3.000 -0.3270 0.00715 0.00150 -0.0007 0.7338 0.3072
-2.750 -0.3016 0.00676 0.00134 -0.0004 0.7252 0.3720
-2.500 -0.2760 0.00646 0.00121 -0.0002 0.7171 0.4287
-2.250 -0.2494 0.00625 0.00113 0.0000 0.7084 0.4710
-2.000 -0.2226 0.00610 0.00107 0.0001 0.7002 0.5072
-1.750 -0.1953 0.00599 0.00101 0.0002 0.6914 0.5323
-1.500 -0.1677 0.00592 0.00098 0.0002 0.6830 0.5539
-1.000 -0.1123 0.00581 0.00092 0.0002 0.6653 0.5880
-0.750 -0.0845 0.00578 0.00090 0.0002 0.6567 0.6026
-0.250 -0.0282 0.00576 0.00088 0.0001 0.6395 0.6222
0.000 0.0000 0.00576 0.00087 0.0000 0.6306 0.6307
0.250 0.0282 0.00576 0.00088 -0.0001 0.6222 0.6396
0.750 0.0845 0.00578 0.00090 -0.0002 0.6025 0.6567
1.000 0.1123 0.00581 0.00092 -0.0002 0.5880 0.6654
1.500 0.1677 0.00592 0.00098 -0.0002 0.5538 0.6830
1.750 0.1953 0.00599 0.00102 -0.0002 0.5323 0.6914
2.000 0.2226 0.00610 0.00107 -0.0001 0.5071 0.7003
2.250 0.2494 0.00625 0.00113 0.0000 0.4708 0.7084
2.500 0.2759 0.00646 0.00121 0.0002 0.4283 0.7172
2.750 0.3016 0.00676 0.00134 0.0004 0.3727 0.7252
3.000 0.3270 0.00714 0.00150 0.0007 0.3082 0.7338
3.250 0.3514 0.00761 0.00171 0.0011 0.2342 0.7423
3.500 0.3762 0.00808 0.00194 0.0014 0.1681 0.7508
3.750 0.4014 0.00847 0.00215 0.0016 0.1175 0.7599
4.000 0.4274 0.00876 0.00235 0.0018 0.0871 0.7688
4.250 0.4536 0.00901 0.00254 0.0020 0.0655 0.7787
4.500 0.4798 0.00924 0.00274 0.0022 0.0505 0.7889
4.750 0.5062 0.00945 0.00294 0.0023 0.0401 0.7993
5.250 0.5588 0.00984 0.00337 0.0027 0.0277 0.8234
5.500 0.5850 0.01002 0.00359 0.0029 0.0240 0.8370
5.750 0.6107 0.01023 0.00383 0.0032 0.0208 0.8520
6.000 0.6364 0.01042 0.00408 0.0036 0.0185 0.8680
6.250 0.6615 0.01067 0.00438 0.0040 0.0164 0.8857
6.500 0.6866 0.01087 0.00466 0.0045 0.0157 0.9041
6.750 0.7115 0.01109 0.00496 0.0050 0.0149 0.9240
7.000 0.7371 0.01136 0.00528 0.0054 0.0142 0.9435
7.250 0.7649 0.01168 0.00564 0.0051 0.0135 0.9605
7.500 0.7947 0.01210 0.00609 0.0044 0.0127 0.9734
7.750 0.8258 0.01251 0.00654 0.0034 0.0123 0.9829
8.000 0.8569 0.01291 0.00697 0.0023 0.0120 0.9903
8.250 0.8874 0.01333 0.00745 0.0013 0.0117 0.9965
8.500 0.9152 0.01377 0.00792 0.0009 0.0115 1.0000
8.750 0.9363 0.01419 0.00838 0.0019 0.0112 1.0000
9.000 0.9578 0.01463 0.00885 0.0028 0.0110 1.0000
9.250 0.9794 0.01508 0.00934 0.0037 0.0108 1.0000
9.500 1.0013 0.01553 0.00983 0.0045 0.0105 1.0000
9.750 1.0231 0.01600 0.01033 0.0052 0.0102 1.0000
10.000 1.0442 0.01653 0.01090 0.0060 0.0100 1.0000
10.250 1.0645 0.01716 0.01158 0.0069 0.0097 1.0000
10.500 1.0833 0.01792 0.01240 0.0080 0.0095 1.0000
10.750 1.0998 0.01888 0.01345 0.0093 0.0092 1.0000
11.000 1.1198 0.01949 0.01412 0.0102 0.0092 1.0000
11.250 1.1391 0.02012 0.01483 0.0111 0.0091 1.0000
11.500 1.1579 0.02077 0.01555 0.0120 0.0090 1.0000
11.750 1.1760 0.02144 0.01629 0.0130 0.0088 1.0000
12.000 1.1927 0.02213 0.01705 0.0142 0.0086 1.0000
12.250 1.2074 0.02287 0.01786 0.0157 0.0084 1.0000
12.500 1.2208 0.02369 0.01876 0.0172 0.0083 1.0000
12.750 1.2329 0.02461 0.01977 0.0186 0.0081 1.0000
13.000 1.2444 0.02561 0.02086 0.0200 0.0080 1.0000
13.250 1.2551 0.02670 0.02203 0.0212 0.0079 1.0000
13.500 1.2651 0.02790 0.02331 0.0223 0.0077 1.0000
13.750 1.2744 0.02921 0.02471 0.0232 0.0076 1.0000
14.000 1.2829 0.03065 0.02623 0.0239 0.0075 1.0000
14.250 1.2905 0.03224 0.02791 0.0245 0.0074 1.0000
14.500 1.2970 0.03401 0.02977 0.0249 0.0073 1.0000
14.750 1.3017 0.03602 0.03187 0.0251 0.0072 1.0000
15.000 1.3046 0.03833 0.03428 0.0251 0.0071 1.0000
15.250 1.3047 0.04103 0.03709 0.0249 0.0070 1.0000
15.500 1.3018 0.04421 0.04039 0.0243 0.0069 1.0000
15.750 1.2950 0.04798 0.04429 0.0234 0.0068 1.0000
16.000 1.2839 0.05250 0.04895 0.0219 0.0068 1.0000
16.250 1.2703 0.05758 0.05418 0.0199 0.0067 1.0000
16.500 1.2616 0.06224 0.05897 0.0179 0.0067 1.0000
16.750 1.2498 0.06759 0.06446 0.0153 0.0066 1.0000
17.000 1.2344 0.07384 0.07085 0.0121 0.0066 1.0000
17.250 1.2150 0.08112 0.07828 0.0082 0.0066 1.0000
17.500 1.1915 0.08944 0.08675 0.0037 0.0066 1.0000
17.750 1.1593 0.09988 0.09736 -0.0020 0.0066 1.0000
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