NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-64 (naca001264-il) Reynolds number: 200,000 Max Cl/Cd: 40.28 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264-il-200000-n5.txt Download as CSV file: xf-naca001264-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8927 0.09374 0.08947 -0.0304 1.0000 0.0264
-15.000 -0.9339 0.08114 0.07665 -0.0390 1.0000 0.0261
-14.750 -0.9666 0.07189 0.06716 -0.0449 1.0000 0.0261
-14.500 -0.9943 0.06468 0.05969 -0.0487 1.0000 0.0261
-14.250 -1.0182 0.05890 0.05362 -0.0506 1.0000 0.0263
-14.000 -1.0379 0.05427 0.04871 -0.0511 1.0000 0.0265
-13.750 -1.0446 0.05123 0.04555 -0.0506 1.0000 0.0268
-13.500 -1.0470 0.04887 0.04311 -0.0498 1.0000 0.0272
-13.250 -1.0483 0.04679 0.04092 -0.0486 1.0000 0.0275
-13.000 -1.0494 0.04483 0.03884 -0.0471 1.0000 0.0279
-12.750 -1.0498 0.04302 0.03690 -0.0453 1.0000 0.0284
-12.500 -1.0500 0.04132 0.03503 -0.0431 1.0000 0.0290
-12.250 -1.0498 0.03966 0.03318 -0.0406 1.0000 0.0296
-12.000 -1.0490 0.03807 0.03138 -0.0377 1.0000 0.0304
-11.750 -1.0474 0.03654 0.02962 -0.0346 1.0000 0.0311
-11.500 -1.0445 0.03513 0.02794 -0.0314 1.0000 0.0318
-11.250 -1.0381 0.03383 0.02639 -0.0286 1.0000 0.0323
-11.000 -1.0271 0.03233 0.02483 -0.0267 1.0000 0.0331
-10.750 -1.0153 0.03138 0.02385 -0.0246 1.0000 0.0339
-10.500 -1.0034 0.03052 0.02292 -0.0224 1.0000 0.0347
-10.250 -0.9912 0.02962 0.02191 -0.0201 1.0000 0.0355
-10.000 -0.9783 0.02867 0.02082 -0.0179 1.0000 0.0364
-9.750 -0.9646 0.02774 0.01975 -0.0157 1.0000 0.0372
-9.500 -0.9506 0.02689 0.01876 -0.0135 1.0000 0.0382
-9.250 -0.9361 0.02613 0.01784 -0.0114 1.0000 0.0390
-9.000 -0.9214 0.02510 0.01676 -0.0093 1.0000 0.0398
-8.750 -0.9072 0.02425 0.01587 -0.0072 1.0000 0.0406
-8.500 -0.8931 0.02354 0.01513 -0.0049 1.0000 0.0414
-8.250 -0.8788 0.02293 0.01448 -0.0027 1.0000 0.0424
-8.000 -0.8642 0.02235 0.01385 -0.0004 1.0000 0.0435
-7.750 -0.8495 0.02178 0.01322 0.0018 1.0000 0.0447
-7.500 -0.8346 0.02121 0.01257 0.0040 1.0000 0.0458
-7.250 -0.8196 0.02066 0.01195 0.0063 1.0000 0.0467
-7.000 -0.8048 0.02010 0.01134 0.0085 1.0000 0.0476
-6.750 -0.7802 0.01937 0.01062 0.0086 0.9980 0.0492
-6.500 -0.7505 0.01881 0.01003 0.0077 0.9954 0.0513
-6.250 -0.7204 0.01832 0.00950 0.0068 0.9927 0.0541
-5.750 -0.6617 0.01728 0.00844 0.0053 0.9863 0.0609
-5.500 -0.6300 0.01685 0.00798 0.0041 0.9839 0.0663
-5.250 -0.6027 0.01638 0.00754 0.0038 0.9798 0.0732
-5.000 -0.5729 0.01597 0.00714 0.0030 0.9762 0.0832
-4.750 -0.5415 0.01553 0.00677 0.0019 0.9734 0.0978
-4.500 -0.5127 0.01511 0.00644 0.0013 0.9697 0.1177
-4.250 -0.4853 0.01468 0.00613 0.0010 0.9651 0.1440
-4.000 -0.4546 0.01423 0.00585 -0.0001 0.9619 0.1794
-3.750 -0.4227 0.01374 0.00555 -0.0014 0.9595 0.2244
-3.500 -0.4011 0.01313 0.00527 -0.0006 0.9533 0.2921
-3.250 -0.3792 0.01213 0.00495 0.0000 0.9486 0.4303
-3.000 -0.3548 0.01132 0.00480 0.0005 0.9453 0.5670
-2.750 -0.3331 0.01100 0.00478 0.0020 0.9390 0.6386
-2.500 -0.3044 0.01083 0.00475 0.0020 0.9345 0.6829
-2.250 -0.2725 0.01071 0.00473 0.0014 0.9313 0.7185
-2.000 -0.2418 0.01064 0.00474 0.0011 0.9275 0.7505
-1.750 -0.2157 0.01064 0.00482 0.0018 0.9210 0.7811
-1.500 -0.1845 0.01063 0.00486 0.0015 0.9168 0.8053
-1.250 -0.1505 0.01066 0.00492 0.0007 0.9137 0.8252
-1.000 -0.1242 0.01077 0.00507 0.0015 0.9067 0.8450
-0.750 -0.0926 0.01085 0.00516 0.0012 0.9016 0.8600
-0.500 -0.0589 0.01085 0.00515 0.0003 0.8978 0.8696
-0.250 -0.0317 0.01089 0.00519 0.0006 0.8898 0.8774
0.000 0.0000 0.01086 0.00516 0.0000 0.8842 0.8842
0.250 0.0317 0.01089 0.00519 -0.0006 0.8774 0.8898
0.500 0.0589 0.01085 0.00515 -0.0003 0.8696 0.8978
0.750 0.0926 0.01085 0.00516 -0.0012 0.8600 0.9016
1.000 0.1242 0.01077 0.00507 -0.0015 0.8451 0.9066
1.250 0.1505 0.01066 0.00492 -0.0007 0.8252 0.9137
1.500 0.1845 0.01063 0.00486 -0.0015 0.8053 0.9168
1.750 0.2157 0.01064 0.00482 -0.0018 0.7811 0.9210
2.000 0.2418 0.01064 0.00474 -0.0011 0.7505 0.9275
2.250 0.2724 0.01071 0.00473 -0.0014 0.7185 0.9313
2.500 0.3044 0.01083 0.00475 -0.0020 0.6830 0.9345
2.750 0.3331 0.01100 0.00478 -0.0019 0.6385 0.9390
3.000 0.3548 0.01132 0.00480 -0.0005 0.5672 0.9453
3.250 0.3792 0.01212 0.00495 0.0000 0.4305 0.9486
3.500 0.4010 0.01312 0.00527 0.0006 0.2921 0.9533
3.750 0.4227 0.01373 0.00555 0.0014 0.2244 0.9595
4.000 0.4546 0.01423 0.00584 0.0001 0.1793 0.9619
4.250 0.4853 0.01468 0.00613 -0.0010 0.1440 0.9652
4.500 0.5127 0.01511 0.00644 -0.0013 0.1177 0.9697
4.750 0.5415 0.01553 0.00676 -0.0019 0.0978 0.9735
5.000 0.5729 0.01596 0.00714 -0.0030 0.0832 0.9762
5.250 0.6027 0.01638 0.00754 -0.0038 0.0733 0.9798
5.500 0.6301 0.01685 0.00798 -0.0041 0.0663 0.9839
5.750 0.6618 0.01728 0.00844 -0.0053 0.0609 0.9864
6.000 0.6912 0.01785 0.00898 -0.0061 0.0569 0.9895
6.250 0.7204 0.01831 0.00950 -0.0068 0.0541 0.9928
6.500 0.7505 0.01880 0.01003 -0.0077 0.0513 0.9954
6.750 0.7803 0.01937 0.01062 -0.0086 0.0492 0.9981
7.000 0.8047 0.02010 0.01134 -0.0085 0.0476 1.0000
7.250 0.8195 0.02065 0.01194 -0.0063 0.0467 1.0000
7.500 0.8345 0.02120 0.01257 -0.0040 0.0458 1.0000
7.750 0.8494 0.02177 0.01322 -0.0018 0.0447 1.0000
8.000 0.8641 0.02234 0.01385 0.0005 0.0436 1.0000
8.250 0.8787 0.02292 0.01447 0.0027 0.0424 1.0000
8.500 0.8930 0.02354 0.01513 0.0050 0.0414 1.0000
8.750 0.9072 0.02424 0.01587 0.0072 0.0406 1.0000
9.000 0.9213 0.02510 0.01675 0.0094 0.0398 1.0000
9.250 0.9361 0.02612 0.01783 0.0114 0.0390 1.0000
9.500 0.9506 0.02689 0.01875 0.0135 0.0382 1.0000
9.750 0.9647 0.02773 0.01975 0.0157 0.0372 1.0000
10.000 0.9783 0.02866 0.02082 0.0179 0.0364 1.0000
10.250 0.9913 0.02962 0.02191 0.0201 0.0355 1.0000
10.500 1.0036 0.03052 0.02291 0.0223 0.0347 1.0000
10.750 1.0155 0.03138 0.02384 0.0245 0.0339 1.0000
11.000 1.0273 0.03233 0.02483 0.0266 0.0331 1.0000
11.250 1.0384 0.03384 0.02640 0.0285 0.0323 1.0000
11.500 1.0448 0.03513 0.02794 0.0314 0.0318 1.0000
12.000 1.0495 0.03807 0.03139 0.0376 0.0304 1.0000
12.250 1.0504 0.03966 0.03319 0.0404 0.0296 1.0000
12.500 1.0507 0.04132 0.03503 0.0430 0.0290 1.0000
12.750 1.0507 0.04302 0.03689 0.0451 0.0284 1.0000
13.000 1.0503 0.04483 0.03884 0.0470 0.0279 1.0000
13.250 1.0493 0.04678 0.04091 0.0485 0.0275 1.0000
13.500 1.0482 0.04886 0.04309 0.0496 0.0271 1.0000
13.750 1.0458 0.05122 0.04555 0.0504 0.0268 1.0000
14.000 1.0389 0.05430 0.04873 0.0509 0.0265 1.0000
14.250 1.0188 0.05898 0.05371 0.0504 0.0263 1.0000
14.500 0.9948 0.06481 0.05983 0.0483 0.0261 1.0000
14.750 0.9671 0.07205 0.06734 0.0446 0.0261 1.0000
15.000 0.9343 0.08141 0.07694 0.0385 0.0261 1.0000
15.250 0.8921 0.09429 0.09003 0.0297 0.0264 1.0000
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