NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA 64(1)-212 MOD A (n64212ma-il) Reynolds number: 200,000 Max Cl/Cd: 49.23 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212ma-il-200000.txt Download as CSV file: xf-n64212ma-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3749 0.09948 0.09575 -0.0291 1.0000 0.0486
-9.500 -0.3768 0.09549 0.09179 -0.0318 1.0000 0.0500
-9.250 -0.4091 0.08770 0.08406 -0.0436 1.0000 0.0509
-9.000 -0.3996 0.08458 0.08100 -0.0422 1.0000 0.0513
-8.750 -0.3838 0.08308 0.07953 -0.0390 1.0000 0.0520
-8.500 -0.3825 0.07984 0.07634 -0.0400 1.0000 0.0526
-8.250 -0.3891 0.07592 0.07248 -0.0425 1.0000 0.0534
-8.000 -0.4087 0.07256 0.06918 -0.0435 1.0000 0.0537
-7.750 -0.4388 0.07118 0.06788 -0.0398 1.0000 0.0537
-7.500 -0.4483 0.06828 0.06494 -0.0407 0.9954 0.0548
-7.250 -0.4333 0.06131 0.05759 -0.0504 0.9834 0.0577
-7.000 -0.4033 0.05773 0.05402 -0.0541 0.9777 0.0592
-6.750 -0.3794 0.05295 0.04859 -0.0606 0.9681 0.0640
-6.500 -0.3498 0.04916 0.04492 -0.0632 0.9610 0.0650
-6.250 -0.3196 0.04731 0.04250 -0.0662 0.9521 0.0709
-6.000 -0.2977 0.04308 0.03832 -0.0676 0.9421 0.0721
-5.750 -0.2700 0.04046 0.03571 -0.0691 0.9345 0.0741
-5.500 -0.2519 0.03865 0.03348 -0.0684 0.9211 0.0805
-5.250 -0.2306 0.03643 0.03132 -0.0682 0.9106 0.0829
-5.000 -0.2112 0.03492 0.02943 -0.0671 0.8990 0.0903
-4.750 -0.1911 0.03298 0.02752 -0.0664 0.8876 0.0930
-4.500 -0.1703 0.03156 0.02580 -0.0653 0.8778 0.1016
-4.250 -0.1486 0.03003 0.02426 -0.0646 0.8672 0.1063
-4.000 -0.1270 0.02850 0.02256 -0.0637 0.8577 0.1159
-3.750 -0.1050 0.02728 0.02118 -0.0630 0.8476 0.1286
-3.500 -0.0826 0.02605 0.01985 -0.0622 0.8373 0.1437
-3.250 -0.0604 0.02469 0.01844 -0.0615 0.8269 0.1613
-2.750 0.0086 0.02035 0.01259 -0.0572 0.8084 0.0717
-2.500 0.0352 0.01908 0.01134 -0.0565 0.7974 0.0690
-2.250 0.0621 0.01799 0.01013 -0.0555 0.7885 0.0670
-2.000 0.0888 0.01719 0.00927 -0.0548 0.7783 0.0669
-1.750 0.1153 0.01654 0.00855 -0.0540 0.7681 0.0682
-1.500 0.1416 0.01588 0.00786 -0.0532 0.7570 0.0685
-1.250 0.1675 0.01527 0.00720 -0.0522 0.7450 0.0689
-1.000 0.1936 0.01475 0.00667 -0.0515 0.7341 0.0699
-0.750 0.2196 0.01432 0.00619 -0.0506 0.7221 0.0711
-0.500 0.2446 0.01371 0.00568 -0.0500 0.7085 0.0741
-0.250 0.2707 0.01337 0.00529 -0.0493 0.6960 0.0785
0.000 0.2966 0.01292 0.00487 -0.0488 0.6806 0.0829
0.250 0.3235 0.01263 0.00454 -0.0484 0.6671 0.0899
0.500 0.3501 0.01231 0.00420 -0.0478 0.6500 0.1099
0.750 0.3635 0.01044 0.00441 -0.0450 0.6326 0.7405
1.000 0.3829 0.01056 0.00460 -0.0421 0.6112 0.7991
1.250 0.4027 0.01068 0.00470 -0.0394 0.5858 0.8306
1.500 0.4208 0.01083 0.00477 -0.0365 0.5512 0.8556
1.750 0.4358 0.01105 0.00481 -0.0330 0.4983 0.8796
2.000 0.4418 0.01187 0.00493 -0.0283 0.3511 0.9025
2.250 0.4503 0.01260 0.00520 -0.0243 0.2611 0.9247
2.500 0.4679 0.01298 0.00537 -0.0222 0.2214 0.9432
2.750 0.4948 0.01337 0.00555 -0.0222 0.1963 0.9571
3.000 0.5287 0.01374 0.00577 -0.0237 0.1818 0.9691
3.250 0.5680 0.01409 0.00602 -0.0263 0.1731 0.9796
3.500 0.6095 0.01453 0.00633 -0.0295 0.1677 0.9892
3.750 0.6488 0.01487 0.00662 -0.0323 0.1643 1.0000
4.000 0.6608 0.01508 0.00679 -0.0300 0.1621 1.0000
4.250 0.6829 0.01538 0.00703 -0.0294 0.1594 1.0000
4.500 0.7073 0.01576 0.00731 -0.0292 0.1568 1.0000
4.750 0.7324 0.01616 0.00764 -0.0291 0.1542 1.0000
5.000 0.7585 0.01647 0.00794 -0.0291 0.1518 1.0000
5.250 0.7843 0.01682 0.00825 -0.0290 0.1494 1.0000
5.500 0.8097 0.01719 0.00859 -0.0288 0.1475 1.0000
5.750 0.8347 0.01761 0.00895 -0.0286 0.1459 1.0000
6.000 0.8593 0.01811 0.00937 -0.0283 0.1445 1.0000
6.250 0.8847 0.01850 0.00978 -0.0280 0.1434 1.0000
6.500 0.9099 0.01891 0.01022 -0.0278 0.1421 1.0000
6.750 0.9348 0.01931 0.01063 -0.0275 0.1406 1.0000
7.000 0.9593 0.01971 0.01103 -0.0272 0.1387 1.0000
7.250 0.9836 0.02014 0.01144 -0.0268 0.1372 1.0000
7.500 1.0075 0.02063 0.01189 -0.0265 0.1355 1.0000
7.750 1.0317 0.02109 0.01239 -0.0261 0.1341 1.0000
8.000 1.0553 0.02151 0.01288 -0.0256 0.1322 1.0000
8.250 1.0780 0.02190 0.01330 -0.0251 0.1297 1.0000
8.500 1.1002 0.02235 0.01372 -0.0245 0.1275 1.0000
8.750 1.1226 0.02285 0.01426 -0.0240 0.1255 1.0000
9.000 1.1438 0.02328 0.01478 -0.0232 0.1229 1.0000
9.250 1.1643 0.02376 0.01525 -0.0224 0.1202 1.0000
9.500 1.1843 0.02432 0.01585 -0.0216 0.1175 1.0000
9.750 1.2025 0.02483 0.01641 -0.0205 0.1142 1.0000
10.000 1.2201 0.02549 0.01706 -0.0194 0.1108 1.0000
10.250 1.2357 0.02615 0.01774 -0.0180 0.1067 1.0000
10.500 1.2497 0.02692 0.01858 -0.0165 0.1024 1.0000
10.750 1.2636 0.02777 0.01945 -0.0151 0.0978 1.0000
11.000 1.2758 0.02863 0.02033 -0.0135 0.0932 1.0000
11.250 1.2848 0.02943 0.02127 -0.0117 0.0888 1.0000
11.500 1.2936 0.03020 0.02228 -0.0100 0.0843 1.0000
12.250 1.3332 0.03260 0.02520 -0.0066 0.0697 1.0000
12.500 1.3462 0.03346 0.02612 -0.0057 0.0670 1.0000
12.750 1.3581 0.03444 0.02713 -0.0049 0.0651 1.0000
13.000 1.3688 0.03557 0.02827 -0.0042 0.0636 1.0000
13.250 1.3776 0.03695 0.02967 -0.0034 0.0624 1.0000
13.500 1.3842 0.03860 0.03136 -0.0027 0.0613 1.0000
13.750 1.3886 0.04050 0.03326 -0.0020 0.0602 1.0000
14.000 1.3910 0.04265 0.03541 -0.0015 0.0593 1.0000
14.250 1.3933 0.04496 0.03779 -0.0010 0.0583 1.0000
14.500 1.3955 0.04733 0.04021 -0.0007 0.0576 1.0000
14.750 1.3972 0.04981 0.04268 -0.0004 0.0568 1.0000
15.000 1.4009 0.05221 0.04505 -0.0002 0.0560 1.0000
15.250 1.4038 0.05476 0.04772 -0.0001 0.0552 1.0000
15.500 1.4088 0.05714 0.05016 0.0000 0.0544 1.0000
15.750 1.4220 0.05878 0.05172 0.0004 0.0536 1.0000
16.000 1.4427 0.05990 0.05275 0.0011 0.0528 1.0000
16.250 1.4417 0.06297 0.05602 0.0008 0.0523 1.0000
16.500 1.4436 0.06588 0.05909 0.0004 0.0518 1.0000
16.750 1.4529 0.06816 0.06143 0.0003 0.0510 1.0000
17.000 1.4948 0.06795 0.06102 0.0018 0.0498 1.0000
17.250 1.4792 0.07236 0.06571 0.0005 0.0495 1.0000
17.500 1.4642 0.07711 0.07073 -0.0011 0.0493 1.0000
17.750 1.4497 0.08216 0.07604 -0.0032 0.0490 1.0000
18.000 1.4334 0.08778 0.08190 -0.0058 0.0488 1.0000
18.250 1.4161 0.09388 0.08824 -0.0090 0.0486 1.0000
18.500 1.3962 0.10075 0.09536 -0.0129 0.0485 1.0000
18.750 1.3708 0.10896 0.10385 -0.0181 0.0484 1.0000
19.000 1.3370 0.11942 0.11460 -0.0253 0.0485 1.0000
19.250 1.2846 0.13477 0.13032 -0.0365 0.0490 1.0000
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