NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 100,000 Max Cl/Cd: 38.73 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212ma-il-100000-n5.txt Download as CSV file: xf-n64212ma-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD A
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3817 0.10958 0.10421 -0.0258 1.0000 0.0601
-10.000 -0.3835 0.10596 0.10063 -0.0285 1.0000 0.0626
-9.750 -0.3991 0.10130 0.09605 -0.0345 1.0000 0.0636
-9.500 -0.3898 0.09779 0.09259 -0.0341 1.0000 0.0641
-9.250 -0.3792 0.09490 0.08973 -0.0334 1.0000 0.0652
-9.000 -0.3754 0.09167 0.08655 -0.0343 1.0000 0.0663
-8.750 -0.3757 0.08812 0.08307 -0.0360 1.0000 0.0676
-8.500 -0.3815 0.08409 0.07911 -0.0389 1.0000 0.0689
-8.250 -0.4014 0.07945 0.07455 -0.0432 1.0000 0.0699
-8.000 -0.4273 0.07648 0.07162 -0.0438 1.0000 0.0704
-7.750 -0.4566 0.07437 0.06949 -0.0421 1.0000 0.0708
-7.500 -0.4573 0.07014 0.06507 -0.0452 0.9889 0.0713
-7.250 -0.4323 0.06615 0.06118 -0.0470 0.9824 0.0724
-7.000 -0.4112 0.06242 0.05738 -0.0501 0.9729 0.0742
-6.750 -0.3965 0.05829 0.05274 -0.0554 0.9601 0.0800
-6.250 -0.3501 0.04671 0.04038 -0.0592 0.9418 0.0503
-6.000 -0.3235 0.04357 0.03703 -0.0610 0.9347 0.0490
-5.750 -0.3026 0.04067 0.03382 -0.0612 0.9238 0.0478
-5.500 -0.2762 0.03761 0.03034 -0.0620 0.9166 0.0467
-5.250 -0.2542 0.03580 0.02832 -0.0618 0.9063 0.0478
-5.000 -0.2272 0.03380 0.02601 -0.0621 0.8982 0.0488
-4.750 -0.2037 0.03196 0.02388 -0.0615 0.8874 0.0489
-4.500 -0.1765 0.03011 0.02172 -0.0613 0.8782 0.0487
-4.250 -0.1519 0.02857 0.01992 -0.0605 0.8671 0.0486
-4.000 -0.1250 0.02711 0.01820 -0.0600 0.8574 0.0488
-3.750 -0.0995 0.02586 0.01672 -0.0592 0.8466 0.0491
-3.500 -0.0730 0.02477 0.01536 -0.0584 0.8363 0.0503
-3.250 -0.0470 0.02380 0.01428 -0.0578 0.8266 0.0517
-3.000 -0.0212 0.02293 0.01336 -0.0571 0.8162 0.0528
-2.750 0.0060 0.02204 0.01238 -0.0564 0.8080 0.0534
-2.500 0.0315 0.02129 0.01159 -0.0556 0.7978 0.0542
-2.250 0.0581 0.02056 0.01081 -0.0549 0.7902 0.0552
-2.000 0.0841 0.01995 0.01015 -0.0541 0.7824 0.0564
-1.750 0.1088 0.01936 0.00964 -0.0533 0.7723 0.0585
-1.500 0.1341 0.01882 0.00912 -0.0524 0.7631 0.0611
-1.250 0.1578 0.01838 0.00868 -0.0513 0.7506 0.0631
-1.000 0.1823 0.01787 0.00817 -0.0502 0.7398 0.0651
-0.750 0.2063 0.01748 0.00776 -0.0493 0.7256 0.0677
-0.500 0.2316 0.01714 0.00734 -0.0484 0.7122 0.0721
-0.250 0.2572 0.01681 0.00695 -0.0477 0.6990 0.0785
0.000 0.2828 0.01651 0.00664 -0.0471 0.6848 0.0863
0.250 0.3089 0.01615 0.00632 -0.0465 0.6715 0.1066
0.500 0.3233 0.01429 0.00641 -0.0442 0.6581 0.6563
0.750 0.3414 0.01427 0.00665 -0.0409 0.6436 0.7494
1.000 0.3599 0.01433 0.00675 -0.0378 0.6264 0.7990
1.250 0.3769 0.01439 0.00683 -0.0344 0.6078 0.8379
1.500 0.3931 0.01444 0.00686 -0.0308 0.5857 0.8725
1.750 0.4134 0.01446 0.00677 -0.0285 0.5518 0.8940
2.000 0.4367 0.01454 0.00662 -0.0272 0.5033 0.9069
2.250 0.4570 0.01494 0.00643 -0.0256 0.3924 0.9194
2.500 0.4772 0.01569 0.00660 -0.0246 0.3022 0.9328
2.750 0.5033 0.01629 0.00687 -0.0248 0.2574 0.9465
3.000 0.5343 0.01678 0.00714 -0.0258 0.2298 0.9605
3.250 0.5685 0.01720 0.00742 -0.0276 0.2095 0.9754
3.500 0.6027 0.01763 0.00770 -0.0294 0.1946 0.9975
3.750 0.6226 0.01799 0.00797 -0.0285 0.1854 1.0000
4.000 0.6437 0.01840 0.00827 -0.0277 0.1782 1.0000
4.250 0.6664 0.01879 0.00860 -0.0272 0.1720 1.0000
4.750 0.7126 0.01966 0.00932 -0.0261 0.1633 1.0000
5.000 0.7361 0.02009 0.00971 -0.0257 0.1599 1.0000
5.250 0.7594 0.02056 0.01011 -0.0252 0.1572 1.0000
5.750 0.8065 0.02153 0.01101 -0.0242 0.1533 1.0000
6.000 0.8304 0.02202 0.01150 -0.0238 0.1516 1.0000
6.250 0.8543 0.02252 0.01199 -0.0234 0.1499 1.0000
6.500 0.8779 0.02303 0.01248 -0.0230 0.1477 1.0000
6.750 0.9009 0.02355 0.01297 -0.0225 0.1453 1.0000
7.000 0.9242 0.02405 0.01349 -0.0220 0.1425 1.0000
7.250 0.9473 0.02455 0.01402 -0.0216 0.1395 1.0000
7.500 0.9696 0.02506 0.01455 -0.0210 0.1368 1.0000
7.750 0.9915 0.02562 0.01508 -0.0205 0.1347 1.0000
8.000 1.0143 0.02619 0.01574 -0.0200 0.1326 1.0000
8.250 1.0362 0.02676 0.01637 -0.0194 0.1304 1.0000
8.500 1.0571 0.02734 0.01699 -0.0187 0.1282 1.0000
8.750 1.0775 0.02797 0.01761 -0.0180 0.1264 1.0000
9.000 1.0985 0.02861 0.01838 -0.0174 0.1242 1.0000
9.250 1.1178 0.02925 0.01909 -0.0166 0.1217 1.0000
9.500 1.1348 0.02991 0.01974 -0.0155 0.1192 1.0000
9.750 1.1517 0.03061 0.02057 -0.0144 0.1162 1.0000
10.000 1.1669 0.03134 0.02134 -0.0131 0.1135 1.0000
10.250 1.1820 0.03217 0.02220 -0.0119 0.1108 1.0000
10.500 1.1962 0.03304 0.02319 -0.0107 0.1078 1.0000
10.750 1.2098 0.03400 0.02413 -0.0096 0.1052 1.0000
11.000 1.2221 0.03503 0.02533 -0.0084 0.1019 1.0000
11.250 1.2333 0.03615 0.02649 -0.0072 0.0986 1.0000
11.500 1.2433 0.03735 0.02787 -0.0060 0.0952 1.0000
11.750 1.2520 0.03866 0.02936 -0.0048 0.0917 1.0000
12.000 1.2591 0.04006 0.03093 -0.0037 0.0878 1.0000
12.250 1.2656 0.04159 0.03271 -0.0027 0.0835 1.0000
12.500 1.2741 0.04334 0.03488 -0.0019 0.0766 1.0000
12.750 1.2820 0.04531 0.03720 -0.0011 0.0690 1.0000
13.000 1.2875 0.04701 0.03901 -0.0006 0.0653 1.0000
13.250 1.2921 0.04871 0.04078 -0.0003 0.0632 1.0000
13.500 1.2947 0.05067 0.04278 -0.0001 0.0617 1.0000
13.750 1.2952 0.05302 0.04514 -0.0002 0.0604 1.0000
14.000 1.2934 0.05579 0.04796 -0.0006 0.0594 1.0000
14.250 1.2885 0.05915 0.05139 -0.0012 0.0585 1.0000
14.500 1.2814 0.06296 0.05530 -0.0022 0.0577 1.0000
14.750 1.2719 0.06729 0.05973 -0.0036 0.0571 1.0000
15.000 1.2603 0.07216 0.06471 -0.0055 0.0566 1.0000
15.250 1.2474 0.07758 0.07023 -0.0080 0.0562 1.0000
15.500 1.2319 0.08382 0.07664 -0.0110 0.0559 1.0000
15.750 1.2141 0.09090 0.08391 -0.0148 0.0555 1.0000
16.000 1.1938 0.09891 0.09211 -0.0193 0.0553 1.0000
16.250 1.1720 0.10762 0.10101 -0.0243 0.0550 1.0000
16.500 1.1504 0.11662 0.11018 -0.0296 0.0547 1.0000
16.750 1.1292 0.12572 0.11945 -0.0349 0.0544 1.0000
17.000 1.1080 0.13505 0.12892 -0.0403 0.0539 1.0000
17.250 1.1000 0.14133 0.13527 -0.0439 0.0534 1.0000
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