NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63012A AIRFOIL (n63012a-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.66 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63012a-il-1000000.txt Download as CSV file: xf-n63012a-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9546 0.11497 0.11307 0.0090 1.0000 0.0096
-16.000 -0.9749 0.10506 0.10305 0.0032 1.0000 0.0095
-15.750 -0.9925 0.09625 0.09412 -0.0022 1.0000 0.0095
-15.500 -1.0092 0.08811 0.08586 -0.0073 1.0000 0.0095
-15.250 -1.0250 0.08073 0.07836 -0.0120 1.0000 0.0094
-15.000 -1.0437 0.07336 0.07084 -0.0165 1.0000 0.0094
-14.750 -1.0630 0.06655 0.06387 -0.0204 1.0000 0.0094
-14.500 -1.0826 0.06018 0.05732 -0.0237 1.0000 0.0094
-14.250 -1.1066 0.05369 0.05061 -0.0264 1.0000 0.0094
-14.000 -1.1303 0.04772 0.04439 -0.0280 1.0000 0.0095
-13.750 -1.1513 0.04249 0.03891 -0.0285 1.0000 0.0096
-13.500 -1.1658 0.03830 0.03449 -0.0281 1.0000 0.0097
-13.250 -1.1714 0.03530 0.03133 -0.0272 1.0000 0.0098
-13.000 -1.1706 0.03312 0.02902 -0.0262 1.0000 0.0100
-12.750 -1.1663 0.03140 0.02721 -0.0250 1.0000 0.0101
-12.500 -1.1597 0.02998 0.02569 -0.0237 1.0000 0.0103
-12.250 -1.1517 0.02874 0.02436 -0.0221 1.0000 0.0104
-12.000 -1.1426 0.02759 0.02312 -0.0205 1.0000 0.0106
-11.750 -1.1322 0.02652 0.02195 -0.0187 1.0000 0.0108
-11.500 -1.1203 0.02548 0.02081 -0.0170 1.0000 0.0110
-11.250 -1.1055 0.02444 0.01968 -0.0157 1.0000 0.0113
-11.000 -1.0892 0.02348 0.01862 -0.0145 1.0000 0.0115
-10.750 -1.0715 0.02263 0.01767 -0.0134 1.0000 0.0118
-10.500 -1.0527 0.02186 0.01681 -0.0125 1.0000 0.0121
-10.250 -1.0334 0.02110 0.01596 -0.0115 1.0000 0.0123
-10.000 -1.0133 0.02040 0.01517 -0.0107 1.0000 0.0124
-9.750 -0.9966 0.01911 0.01378 -0.0093 1.0000 0.0126
-9.500 -0.9829 0.01756 0.01212 -0.0075 1.0000 0.0131
-9.250 -0.9643 0.01672 0.01123 -0.0063 1.0000 0.0135
-9.000 -0.9440 0.01610 0.01058 -0.0053 1.0000 0.0138
-8.750 -0.9233 0.01555 0.00999 -0.0043 1.0000 0.0142
-8.500 -0.9028 0.01502 0.00943 -0.0033 1.0000 0.0146
-8.250 -0.8823 0.01456 0.00894 -0.0021 1.0000 0.0151
-8.000 -0.8621 0.01414 0.00847 -0.0008 1.0000 0.0156
-7.750 -0.8425 0.01372 0.00801 0.0005 1.0000 0.0160
-7.500 -0.8232 0.01334 0.00759 0.0020 1.0000 0.0162
-7.250 -0.8064 0.01258 0.00677 0.0038 0.9996 0.0169
-7.000 -0.7731 0.01196 0.00612 0.0022 0.9967 0.0180
-6.750 -0.7381 0.01154 0.00568 0.0003 0.9941 0.0190
-6.500 -0.7049 0.01117 0.00529 -0.0011 0.9897 0.0202
-6.250 -0.6708 0.01075 0.00484 -0.0027 0.9852 0.0217
-6.000 -0.6390 0.01033 0.00443 -0.0039 0.9781 0.0249
-5.750 -0.6061 0.00996 0.00404 -0.0052 0.9704 0.0290
-5.500 -0.5770 0.00963 0.00373 -0.0056 0.9579 0.0354
-5.250 -0.5500 0.00929 0.00342 -0.0055 0.9429 0.0466
-5.000 -0.5249 0.00898 0.00315 -0.0050 0.9259 0.0628
-4.750 -0.5006 0.00864 0.00289 -0.0044 0.9086 0.0892
-4.500 -0.4769 0.00822 0.00261 -0.0038 0.8914 0.1327
-4.250 -0.4539 0.00770 0.00231 -0.0031 0.8753 0.1969
-4.000 -0.4310 0.00714 0.00202 -0.0024 0.8603 0.2769
-3.750 -0.4082 0.00658 0.00177 -0.0017 0.8465 0.3657
-3.500 -0.3841 0.00618 0.00160 -0.0012 0.8336 0.4395
-3.250 -0.3584 0.00595 0.00149 -0.0008 0.8215 0.4868
-3.000 -0.3316 0.00583 0.00141 -0.0006 0.8105 0.5145
-2.750 -0.3046 0.00574 0.00134 -0.0005 0.8001 0.5367
-2.500 -0.2775 0.00567 0.00128 -0.0003 0.7897 0.5596
-2.250 -0.2502 0.00559 0.00123 -0.0002 0.7801 0.5805
-2.000 -0.2230 0.00554 0.00119 -0.0001 0.7707 0.6008
-1.750 -0.1953 0.00549 0.00116 0.0000 0.7612 0.6172
-1.500 -0.1676 0.00546 0.00113 0.0000 0.7521 0.6323
-1.250 -0.1400 0.00544 0.00110 0.0001 0.7430 0.6457
-1.000 -0.1121 0.00541 0.00109 0.0001 0.7338 0.6584
-0.750 -0.0842 0.00541 0.00107 0.0001 0.7251 0.6702
-0.500 -0.0560 0.00540 0.00106 0.0000 0.7160 0.6804
-0.250 -0.0281 0.00538 0.00105 0.0000 0.7074 0.6893
0.000 0.0000 0.00540 0.00105 0.0000 0.6983 0.6983
0.250 0.0281 0.00538 0.00105 0.0000 0.6893 0.7074
0.500 0.0561 0.00540 0.00106 -0.0001 0.6804 0.7159
0.750 0.0843 0.00541 0.00107 -0.0001 0.6702 0.7251
1.000 0.1121 0.00541 0.00109 -0.0001 0.6584 0.7338
1.250 0.1400 0.00544 0.00110 -0.0001 0.6457 0.7430
1.500 0.1677 0.00546 0.00113 0.0000 0.6323 0.7521
1.750 0.1954 0.00549 0.00116 0.0000 0.6170 0.7612
2.000 0.2230 0.00554 0.00119 0.0001 0.6007 0.7707
2.250 0.2503 0.00559 0.00123 0.0002 0.5804 0.7800
2.500 0.2776 0.00567 0.00128 0.0003 0.5598 0.7897
2.750 0.3048 0.00574 0.00134 0.0004 0.5367 0.8001
3.000 0.3318 0.00583 0.00141 0.0006 0.5145 0.8105
3.250 0.3586 0.00595 0.00149 0.0008 0.4867 0.8215
3.750 0.4084 0.00658 0.00177 0.0017 0.3651 0.8465
4.000 0.4314 0.00714 0.00203 0.0023 0.2763 0.8602
4.250 0.4542 0.00771 0.00232 0.0030 0.1961 0.8752
4.500 0.4773 0.00823 0.00261 0.0037 0.1322 0.8913
4.750 0.5011 0.00865 0.00289 0.0043 0.0887 0.9084
5.000 0.5254 0.00898 0.00315 0.0049 0.0626 0.9258
5.250 0.5505 0.00930 0.00342 0.0054 0.0465 0.9427
5.500 0.5773 0.00963 0.00373 0.0055 0.0353 0.9578
5.750 0.6063 0.00996 0.00405 0.0051 0.0289 0.9703
6.000 0.6391 0.01033 0.00442 0.0038 0.0248 0.9782
6.250 0.6710 0.01075 0.00483 0.0027 0.0217 0.9853
6.500 0.7050 0.01117 0.00529 0.0011 0.0202 0.9898
6.750 0.7383 0.01154 0.00568 -0.0004 0.0190 0.9942
7.000 0.7733 0.01196 0.00612 -0.0022 0.0179 0.9968
7.250 0.8065 0.01258 0.00677 -0.0039 0.0169 0.9997
7.500 0.8228 0.01333 0.00759 -0.0019 0.0162 1.0000
7.750 0.8422 0.01371 0.00801 -0.0005 0.0160 1.0000
8.000 0.8619 0.01414 0.00846 0.0009 0.0156 1.0000
8.250 0.8822 0.01456 0.00893 0.0021 0.0151 1.0000
8.500 0.9029 0.01503 0.00943 0.0032 0.0146 1.0000
8.750 0.9236 0.01555 0.00999 0.0043 0.0142 1.0000
9.000 0.9444 0.01610 0.01058 0.0052 0.0138 1.0000
9.250 0.9649 0.01673 0.01124 0.0062 0.0135 1.0000
9.500 0.9836 0.01758 0.01214 0.0074 0.0131 1.0000
9.750 0.9973 0.01916 0.01383 0.0092 0.0126 1.0000
10.000 1.0144 0.02040 0.01518 0.0104 0.0124 1.0000
10.250 1.0345 0.02112 0.01598 0.0113 0.0123 1.0000
10.500 1.0541 0.02187 0.01682 0.0122 0.0121 1.0000
10.750 1.0730 0.02265 0.01770 0.0131 0.0118 1.0000
11.000 1.0909 0.02350 0.01864 0.0142 0.0115 1.0000
11.250 1.1073 0.02448 0.01972 0.0153 0.0112 1.0000
11.500 1.1223 0.02551 0.02085 0.0166 0.0110 1.0000
11.750 1.1345 0.02655 0.02199 0.0182 0.0108 1.0000
12.000 1.1450 0.02763 0.02316 0.0200 0.0106 1.0000
12.250 1.1542 0.02878 0.02440 0.0216 0.0104 1.0000
12.500 1.1624 0.03003 0.02574 0.0231 0.0103 1.0000
12.750 1.1689 0.03148 0.02730 0.0245 0.0101 1.0000
13.000 1.1733 0.03319 0.02910 0.0256 0.0100 1.0000
13.250 1.1738 0.03543 0.03146 0.0267 0.0098 1.0000
13.500 1.1678 0.03850 0.03470 0.0275 0.0097 1.0000
13.750 1.1522 0.04284 0.03928 0.0279 0.0096 1.0000
14.000 1.1308 0.04815 0.04485 0.0273 0.0095 1.0000
14.250 1.1060 0.05429 0.05124 0.0255 0.0094 1.0000
14.500 1.0841 0.06054 0.05770 0.0229 0.0094 1.0000
14.750 1.0669 0.06659 0.06392 0.0197 0.0094 1.0000
15.000 1.0447 0.07391 0.07140 0.0155 0.0094 1.0000
15.250 1.0254 0.08144 0.07909 0.0108 0.0094 1.0000
15.500 1.0094 0.08894 0.08671 0.0061 0.0094 1.0000
15.750 0.9941 0.09686 0.09474 0.0011 0.0095 1.0000
16.000 0.9769 0.10562 0.10362 -0.0043 0.0095 1.0000
16.250 0.9549 0.11600 0.11411 -0.0103 0.0096 1.0000
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