NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 100,000 Max Cl/Cd: 40.5 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23012-il-100000-n5.txt Download as CSV file: xf-naca23012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23012 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6027 0.08570 0.08036 -0.0227 1.0000 0.0381
-10.250 -0.6278 0.07628 0.07087 -0.0305 1.0000 0.0375
-10.000 -0.6550 0.06969 0.06416 -0.0341 1.0000 0.0370
-9.750 -0.6791 0.06498 0.05930 -0.0338 1.0000 0.0368
-9.500 -0.6952 0.06054 0.05463 -0.0327 1.0000 0.0366
-9.250 -0.7048 0.05638 0.05021 -0.0312 1.0000 0.0367
-9.000 -0.7080 0.05276 0.04631 -0.0295 1.0000 0.0371
-8.750 -0.7077 0.04937 0.04261 -0.0276 1.0000 0.0378
-8.500 -0.7061 0.04590 0.03873 -0.0253 1.0000 0.0387
-8.250 -0.7021 0.04249 0.03485 -0.0228 1.0000 0.0393
-8.000 -0.6942 0.03945 0.03135 -0.0204 1.0000 0.0398
-7.750 -0.6828 0.03684 0.02835 -0.0181 1.0000 0.0403
-7.500 -0.6670 0.03509 0.02648 -0.0166 1.0000 0.0409
-7.250 -0.6498 0.03378 0.02510 -0.0152 1.0000 0.0419
-7.000 -0.6327 0.03241 0.02356 -0.0135 1.0000 0.0433
-6.750 -0.6154 0.03081 0.02168 -0.0118 1.0000 0.0448
-6.500 -0.5968 0.02912 0.01968 -0.0101 1.0000 0.0460
-6.250 -0.5771 0.02758 0.01787 -0.0085 1.0000 0.0470
-6.000 -0.5572 0.02643 0.01673 -0.0072 1.0000 0.0482
-5.750 -0.5374 0.02556 0.01583 -0.0059 1.0000 0.0501
-5.500 -0.5171 0.02464 0.01482 -0.0045 1.0000 0.0523
-5.250 -0.4962 0.02368 0.01371 -0.0031 1.0000 0.0542
-5.000 -0.4760 0.02270 0.01275 -0.0018 1.0000 0.0559
-4.750 -0.4565 0.02199 0.01209 -0.0004 1.0000 0.0582
-4.500 -0.4369 0.02138 0.01147 0.0010 1.0000 0.0614
-4.250 -0.4165 0.02076 0.01080 0.0023 0.9998 0.0645
-4.000 -0.3789 0.01990 0.01006 -0.0001 0.9930 0.0690
-3.750 -0.3405 0.01929 0.00940 -0.0024 0.9850 0.0755
-3.500 -0.3042 0.01856 0.00874 -0.0044 0.9760 0.0830
-3.250 -0.2666 0.01793 0.00811 -0.0066 0.9669 0.0929
-3.000 -0.2277 0.01730 0.00751 -0.0089 0.9578 0.1083
-2.750 -0.1930 0.01655 0.00693 -0.0104 0.9462 0.1392
-2.500 -0.1697 0.01443 0.00653 -0.0104 0.9339 0.4780
-2.250 -0.1403 0.01376 0.00651 -0.0099 0.9209 0.6301
-2.000 -0.1084 0.01348 0.00651 -0.0095 0.9064 0.7192
-1.750 -0.0760 0.01337 0.00654 -0.0090 0.8893 0.7822
-1.500 -0.0426 0.01338 0.00659 -0.0086 0.8689 0.8316
-1.250 -0.0069 0.01348 0.00665 -0.0085 0.8467 0.8754
-1.000 0.0325 0.01358 0.00663 -0.0094 0.8232 0.9020
-0.750 0.0683 0.01360 0.00649 -0.0103 0.7965 0.9163
-0.500 0.1037 0.01361 0.00633 -0.0112 0.7693 0.9290
-0.250 0.1381 0.01366 0.00619 -0.0119 0.7401 0.9416
0.000 0.1772 0.01371 0.00606 -0.0138 0.7088 0.9510
0.250 0.2151 0.01378 0.00594 -0.0155 0.6760 0.9606
0.500 0.2513 0.01388 0.00583 -0.0170 0.6429 0.9709
0.750 0.2908 0.01398 0.00572 -0.0193 0.6079 0.9790
1.000 0.3288 0.01410 0.00562 -0.0213 0.5731 0.9874
1.250 0.3670 0.01423 0.00555 -0.0236 0.5382 0.9955
1.500 0.3991 0.01438 0.00551 -0.0247 0.5060 1.0000
1.750 0.4210 0.01454 0.00550 -0.0237 0.4787 1.0000
2.000 0.4428 0.01473 0.00553 -0.0227 0.4523 1.0000
2.250 0.4645 0.01494 0.00558 -0.0217 0.4282 1.0000
2.500 0.4863 0.01517 0.00569 -0.0207 0.4056 1.0000
2.750 0.5080 0.01542 0.00581 -0.0196 0.3856 1.0000
3.000 0.5296 0.01570 0.00596 -0.0186 0.3675 1.0000
3.250 0.5514 0.01598 0.00615 -0.0176 0.3514 1.0000
3.500 0.5733 0.01627 0.00636 -0.0165 0.3372 1.0000
3.750 0.5951 0.01659 0.00659 -0.0155 0.3247 1.0000
4.000 0.6168 0.01693 0.00683 -0.0145 0.3136 1.0000
4.250 0.6390 0.01725 0.00714 -0.0135 0.3026 1.0000
4.500 0.6611 0.01761 0.00744 -0.0125 0.2935 1.0000
4.750 0.6832 0.01797 0.00777 -0.0115 0.2845 1.0000
5.000 0.7054 0.01835 0.00813 -0.0106 0.2763 1.0000
5.250 0.7275 0.01874 0.00850 -0.0096 0.2684 1.0000
5.500 0.7498 0.01916 0.00890 -0.0087 0.2614 1.0000
5.750 0.7722 0.01957 0.00934 -0.0078 0.2540 1.0000
6.000 0.7943 0.02004 0.00975 -0.0068 0.2478 1.0000
6.250 0.8170 0.02046 0.01027 -0.0060 0.2408 1.0000
6.500 0.8393 0.02094 0.01073 -0.0051 0.2346 1.0000
6.750 0.8619 0.02143 0.01128 -0.0043 0.2284 1.0000
7.000 0.8843 0.02191 0.01182 -0.0035 0.2219 1.0000
7.250 0.9066 0.02246 0.01232 -0.0027 0.2166 1.0000
7.500 0.9289 0.02296 0.01300 -0.0019 0.2099 1.0000
7.750 0.9509 0.02348 0.01356 -0.0011 0.2041 1.0000
8.000 0.9727 0.02406 0.01421 -0.0003 0.1984 1.0000
8.250 0.9942 0.02462 0.01490 0.0005 0.1920 1.0000
8.500 1.0155 0.02517 0.01544 0.0014 0.1866 1.0000
8.750 1.0363 0.02579 0.01625 0.0023 0.1801 1.0000
9.000 1.0566 0.02634 0.01689 0.0032 0.1741 1.0000
9.250 1.0765 0.02697 0.01761 0.0042 0.1683 1.0000
9.500 1.0957 0.02759 0.01839 0.0052 0.1617 1.0000
9.750 1.1143 0.02819 0.01900 0.0062 0.1563 1.0000
10.000 1.1321 0.02893 0.01998 0.0074 0.1493 1.0000
10.250 1.1490 0.02953 0.02060 0.0086 0.1437 1.0000
10.500 1.1649 0.03037 0.02166 0.0099 0.1369 1.0000
10.750 1.1794 0.03106 0.02242 0.0113 0.1311 1.0000
11.000 1.1929 0.03200 0.02354 0.0128 0.1245 1.0000
11.250 1.2043 0.03285 0.02446 0.0144 0.1188 1.0000
11.500 1.2141 0.03394 0.02571 0.0161 0.1128 1.0000
11.750 1.2201 0.03499 0.02687 0.0183 0.1076 1.0000
12.000 1.2246 0.03630 0.02828 0.0203 0.1027 1.0000
12.250 1.2281 0.03779 0.02993 0.0220 0.0975 1.0000
12.500 1.2290 0.03946 0.03160 0.0234 0.0937 1.0000
12.750 1.2296 0.04157 0.03395 0.0245 0.0889 1.0000
13.000 1.2275 0.04390 0.03639 0.0251 0.0851 1.0000
13.250 1.2235 0.04666 0.03924 0.0252 0.0819 1.0000
13.500 1.2178 0.04997 0.04276 0.0247 0.0784 1.0000
13.750 1.2100 0.05370 0.04663 0.0237 0.0756 1.0000
14.000 1.2008 0.05779 0.05077 0.0221 0.0734 1.0000
14.250 1.1880 0.06283 0.05601 0.0200 0.0712 1.0000
14.500 1.1727 0.06849 0.06186 0.0173 0.0691 1.0000
14.750 1.1559 0.07455 0.06807 0.0143 0.0675 1.0000
15.000 1.1391 0.08077 0.07439 0.0111 0.0659 1.0000
15.250 1.1260 0.08631 0.07997 0.0084 0.0644 1.0000
15.500 1.1046 0.09373 0.08753 0.0047 0.0631 1.0000
15.750 1.0769 0.10268 0.09668 0.0001 0.0621 1.0000
16.000 1.0434 0.11316 0.10735 -0.0054 0.0610 1.0000
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Polar data table (+)
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