NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.93 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64012-il-1000000.txt Download as CSV file: xf-n64012-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY 64-012 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
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0425 0.08111 0.07882 -0.0110 1.0000 0.0098
-15.500 -1.0658 0.07277 0.07031 -0.0163 1.0000 0.0098
-15.250 -1.0851 0.06597 0.06335 -0.0201 1.0000 0.0098
-15.000 -1.1082 0.05916 0.05633 -0.0234 1.0000 0.0098
-14.750 -1.1188 0.05469 0.05175 -0.0253 1.0000 0.0098
-14.500 -1.1331 0.04996 0.04684 -0.0268 1.0000 0.0099
-14.250 -1.1395 0.04653 0.04329 -0.0276 1.0000 0.0100
-14.000 -1.1410 0.04387 0.04056 -0.0279 1.0000 0.0101
-13.750 -1.1500 0.04040 0.03690 -0.0279 1.0000 0.0101
-13.500 -1.1458 0.03868 0.03513 -0.0276 1.0000 0.0103
-13.250 -1.1423 0.03697 0.03335 -0.0271 1.0000 0.0104
-13.000 -1.1414 0.03499 0.03124 -0.0262 1.0000 0.0106
-12.750 -1.1408 0.03301 0.02912 -0.0250 1.0000 0.0106
-12.500 -1.1372 0.03144 0.02744 -0.0236 1.0000 0.0108
-12.250 -1.1318 0.03014 0.02603 -0.0220 1.0000 0.0110
-12.000 -1.1277 0.02858 0.02434 -0.0201 1.0000 0.0111
-11.750 -1.1210 0.02741 0.02306 -0.0181 1.0000 0.0114
-11.500 -1.1130 0.02633 0.02187 -0.0159 1.0000 0.0116
-11.250 -1.1020 0.02525 0.02068 -0.0141 1.0000 0.0118
-11.000 -1.0858 0.02454 0.01988 -0.0129 1.0000 0.0121
-10.750 -1.0688 0.02372 0.01895 -0.0118 1.0000 0.0123
-10.500 -1.0499 0.02316 0.01830 -0.0109 1.0000 0.0124
-10.250 -1.0399 0.02051 0.01544 -0.0092 1.0000 0.0128
-10.000 -1.0226 0.01939 0.01425 -0.0081 1.0000 0.0132
-9.750 -1.0029 0.01860 0.01342 -0.0073 1.0000 0.0135
-9.500 -0.9815 0.01798 0.01277 -0.0067 1.0000 0.0139
-9.250 -0.9598 0.01736 0.01210 -0.0061 1.0000 0.0142
-9.000 -0.9377 0.01674 0.01144 -0.0056 1.0000 0.0146
-8.750 -0.9148 0.01621 0.01086 -0.0051 1.0000 0.0151
-8.500 -0.8914 0.01569 0.01030 -0.0047 1.0000 0.0156
-8.250 -0.8678 0.01518 0.00975 -0.0043 1.0000 0.0159
-8.000 -0.8355 0.01470 0.00921 -0.0057 0.9766 0.0162
-7.750 -0.8120 0.01341 0.00781 -0.0058 0.9516 0.0171
-7.500 -0.7911 0.01297 0.00730 -0.0046 0.9322 0.0177
-7.250 -0.7689 0.01264 0.00691 -0.0037 0.9168 0.0184
-7.000 -0.7457 0.01231 0.00651 -0.0029 0.9034 0.0192
-6.750 -0.7218 0.01200 0.00613 -0.0023 0.8913 0.0200
-6.500 -0.6967 0.01179 0.00586 -0.0019 0.8802 0.0207
-6.000 -0.6490 0.01086 0.00481 -0.0007 0.8587 0.0240
-5.750 -0.6231 0.01062 0.00451 -0.0004 0.8494 0.0256
-5.500 -0.5971 0.01038 0.00421 -0.0002 0.8399 0.0271
-5.250 -0.5717 0.00999 0.00379 0.0001 0.8306 0.0311
-5.000 -0.5451 0.00980 0.00355 0.0003 0.8218 0.0337
-4.750 -0.5188 0.00949 0.00324 0.0004 0.8126 0.0398
-4.500 -0.4923 0.00923 0.00298 0.0006 0.8043 0.0489
-4.250 -0.4664 0.00885 0.00271 0.0007 0.7956 0.0760
-4.000 -0.4412 0.00832 0.00241 0.0009 0.7873 0.1337
-3.750 -0.4175 0.00757 0.00205 0.0012 0.7789 0.2351
-3.500 -0.3950 0.00658 0.00164 0.0015 0.7706 0.3814
-3.250 -0.3695 0.00613 0.00148 0.0017 0.7623 0.4739
-3.000 -0.3418 0.00596 0.00140 0.0016 0.7539 0.5074
-2.750 -0.3139 0.00587 0.00132 0.0016 0.7460 0.5301
-2.500 -0.2855 0.00580 0.00126 0.0014 0.7379 0.5452
-2.250 -0.2572 0.00576 0.00121 0.0013 0.7303 0.5601
-2.000 -0.2287 0.00570 0.00117 0.0012 0.7224 0.5784
-1.750 -0.2006 0.00566 0.00114 0.0011 0.7151 0.5970
-1.500 -0.1723 0.00560 0.00113 0.0010 0.7073 0.6160
-1.250 -0.1437 0.00561 0.00111 0.0009 0.6999 0.6270
-1.000 -0.1150 0.00557 0.00109 0.0007 0.6921 0.6349
-0.750 -0.0864 0.00558 0.00106 0.0006 0.6850 0.6425
-0.500 -0.0576 0.00556 0.00105 0.0004 0.6778 0.6503
-0.250 -0.0289 0.00557 0.00104 0.0002 0.6710 0.6574
0.000 -0.0001 0.00555 0.00104 0.0000 0.6642 0.6642
0.250 0.0287 0.00557 0.00104 -0.0002 0.6574 0.6710
0.500 0.0574 0.00556 0.00105 -0.0004 0.6503 0.6778
0.750 0.0862 0.00558 0.00106 -0.0005 0.6425 0.6850
1.000 0.1149 0.00557 0.00109 -0.0007 0.6349 0.6922
1.250 0.1436 0.00561 0.00111 -0.0009 0.6270 0.7000
1.500 0.1721 0.00560 0.00113 -0.0010 0.6160 0.7073
1.750 0.2004 0.00566 0.00114 -0.0011 0.5969 0.7151
2.000 0.2286 0.00570 0.00117 -0.0012 0.5784 0.7224
2.250 0.2570 0.00576 0.00121 -0.0013 0.5601 0.7304
2.500 0.2853 0.00580 0.00126 -0.0014 0.5452 0.7379
2.750 0.3137 0.00587 0.00132 -0.0015 0.5301 0.7460
3.000 0.3417 0.00596 0.00140 -0.0016 0.5071 0.7539
3.250 0.3694 0.00613 0.00148 -0.0016 0.4739 0.7623
3.500 0.3949 0.00657 0.00164 -0.0015 0.3827 0.7706
3.750 0.4174 0.00756 0.00204 -0.0011 0.2366 0.7789
4.000 0.4411 0.00832 0.00240 -0.0009 0.1347 0.7874
4.250 0.4662 0.00885 0.00271 -0.0007 0.0762 0.7956
4.500 0.4921 0.00923 0.00298 -0.0005 0.0489 0.8043
4.750 0.5186 0.00949 0.00324 -0.0004 0.0398 0.8126
5.000 0.5449 0.00980 0.00355 -0.0002 0.0337 0.8218
5.250 0.5715 0.00999 0.00379 -0.0001 0.0311 0.8306
5.500 0.5971 0.01035 0.00418 0.0002 0.0274 0.8399
5.750 0.6230 0.01061 0.00451 0.0005 0.0256 0.8494
6.000 0.6488 0.01086 0.00481 0.0008 0.0240 0.8587
6.500 0.6967 0.01176 0.00582 0.0019 0.0207 0.8803
6.750 0.7217 0.01198 0.00611 0.0023 0.0200 0.8914
7.000 0.7456 0.01230 0.00650 0.0029 0.0192 0.9036
7.250 0.7687 0.01264 0.00691 0.0037 0.0185 0.9170
7.500 0.7909 0.01298 0.00731 0.0047 0.0178 0.9323
7.750 0.8119 0.01341 0.00781 0.0058 0.0171 0.9518
8.000 0.8357 0.01467 0.00918 0.0057 0.0162 0.9765
8.250 0.8677 0.01518 0.00975 0.0043 0.0159 1.0000
8.500 0.8913 0.01570 0.01032 0.0047 0.0156 1.0000
8.750 0.9152 0.01614 0.01079 0.0050 0.0151 1.0000
9.000 0.9378 0.01673 0.01142 0.0056 0.0146 1.0000
9.250 0.9598 0.01736 0.01210 0.0061 0.0142 1.0000
9.500 0.9815 0.01798 0.01277 0.0067 0.0138 1.0000
9.750 1.0028 0.01860 0.01342 0.0074 0.0135 1.0000
10.000 1.0227 0.01937 0.01423 0.0081 0.0132 1.0000
10.250 1.0386 0.02073 0.01567 0.0093 0.0128 1.0000
10.500 1.0505 0.02300 0.01813 0.0109 0.0124 1.0000
10.750 1.0686 0.02378 0.01902 0.0119 0.0123 1.0000
11.000 1.0857 0.02458 0.01992 0.0129 0.0121 1.0000
11.250 1.1008 0.02551 0.02096 0.0142 0.0118 1.0000
11.500 1.1131 0.02634 0.02188 0.0159 0.0116 1.0000
11.750 1.1199 0.02764 0.02331 0.0182 0.0114 1.0000
12.000 1.1271 0.02872 0.02450 0.0201 0.0112 1.0000
12.250 1.1309 0.03032 0.02623 0.0221 0.0111 1.0000
12.500 1.1363 0.03163 0.02765 0.0236 0.0109 1.0000
12.750 1.1380 0.03346 0.02961 0.0251 0.0108 1.0000
13.000 1.1437 0.03475 0.03099 0.0261 0.0105 1.0000
13.250 1.1419 0.03705 0.03343 0.0271 0.0104 1.0000
13.500 1.1439 0.03897 0.03545 0.0276 0.0103 1.0000
13.750 1.1442 0.04118 0.03776 0.0279 0.0102 1.0000
14.000 1.1474 0.04313 0.03976 0.0279 0.0100 1.0000
14.250 1.1412 0.04637 0.04312 0.0275 0.0099 1.0000
14.500 1.1323 0.05013 0.04702 0.0267 0.0099 1.0000
14.750 1.1206 0.05451 0.05156 0.0253 0.0098 1.0000
15.000 1.1056 0.05964 0.05683 0.0231 0.0098 1.0000
15.250 1.0873 0.06572 0.06310 0.0201 0.0098 1.0000
15.500 1.0679 0.07250 0.07003 0.0163 0.0097 1.0000
15.750 1.0353 0.08274 0.08051 0.0099 0.0099 1.0000
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Polar data table (+)
Polar graphs
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