NACA6409 9% (n6409-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA6409 9% (n6409-il) Reynolds number: 100,000 Max Cl/Cd: 61.59 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6409-il-100000.txt Download as CSV file: xf-n6409-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA6409 9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3419 0.11534 0.11101 -0.0253 1.0000 0.0710
-7.750 -0.3605 0.11553 0.11130 -0.0234 1.0000 0.0713
-7.500 -0.3803 0.11566 0.11152 -0.0212 1.0000 0.0715
-7.250 -0.3942 0.11522 0.11116 -0.0216 1.0000 0.0717
-7.000 -0.4029 0.11420 0.11020 -0.0241 1.0000 0.0719
-6.750 -0.3972 0.10789 0.10394 -0.0177 1.0000 0.0729
-6.500 -0.3818 0.10360 0.09964 -0.0157 0.9982 0.0750
-6.250 -0.3565 0.09959 0.09559 -0.0207 0.9917 0.0788
-6.000 -0.3184 0.09657 0.09249 -0.0431 0.9779 0.0854
-5.750 -0.3002 0.09073 0.08666 -0.0438 0.9730 0.0869
-5.500 -0.2835 0.08706 0.08299 -0.0420 0.9667 0.0899
-5.250 -0.2538 0.08310 0.07899 -0.0485 0.9592 0.0954
-5.000 -0.2147 0.07811 0.07385 -0.0648 0.9478 0.1011
-4.750 -0.1923 0.07430 0.07006 -0.0638 0.9437 0.1042
-4.500 -0.1685 0.07120 0.06688 -0.0680 0.9335 0.1111
-4.250 -0.1291 0.06659 0.06216 -0.0761 0.9279 0.1193
-4.000 -0.0862 0.06259 0.05792 -0.0870 0.9180 0.1311
-3.750 -0.0428 0.05990 0.05496 -0.0941 0.9107 0.1448
-3.500 -0.0229 0.05567 0.05081 -0.0942 0.9037 0.1478
-3.250 0.0241 0.05203 0.04700 -0.1007 0.8999 0.1634
-3.000 0.0502 0.04968 0.04453 -0.1028 0.8894 0.1784
-2.750 0.1305 0.04163 0.03534 -0.1169 0.8868 0.1302
-2.500 0.1772 0.03451 0.02741 -0.1216 0.8825 0.0976
-2.250 0.2152 0.03192 0.02414 -0.1237 0.8751 0.0993
-2.000 0.2621 0.02931 0.02109 -0.1271 0.8717 0.1032
-1.750 0.2899 0.02855 0.02009 -0.1271 0.8617 0.1130
-1.500 0.3352 0.02705 0.01835 -0.1298 0.8576 0.1271
-1.250 0.3637 0.02638 0.01754 -0.1298 0.8480 0.1436
-1.000 0.4080 0.02529 0.01645 -0.1324 0.8436 0.1692
-0.750 0.4579 0.02418 0.01532 -0.1358 0.8412 0.2041
-0.500 0.4815 0.02385 0.01506 -0.1350 0.8298 0.2322
-0.250 0.5291 0.02277 0.01408 -0.1380 0.8269 0.2835
0.000 0.5532 0.02237 0.01386 -0.1371 0.8159 0.3328
0.250 0.6039 0.01980 0.01294 -0.1406 0.8133 1.0000
0.500 0.6312 0.01992 0.01272 -0.1401 0.8027 1.0000
0.750 0.6748 0.01948 0.01202 -0.1423 0.7982 1.0000
1.000 0.6997 0.01964 0.01204 -0.1416 0.7871 1.0000
1.250 0.7430 0.01919 0.01142 -0.1437 0.7826 1.0000
1.500 0.7658 0.01944 0.01159 -0.1427 0.7712 1.0000
1.750 0.7958 0.01948 0.01153 -0.1428 0.7625 1.0000
2.000 0.8301 0.01934 0.01130 -0.1435 0.7549 1.0000
2.250 0.8548 0.01961 0.01151 -0.1428 0.7448 1.0000
2.500 0.8924 0.01939 0.01122 -0.1441 0.7387 1.0000
2.750 0.9136 0.01980 0.01161 -0.1429 0.7279 1.0000
3.000 0.9463 0.01982 0.01158 -0.1435 0.7208 1.0000
3.250 0.9712 0.02011 0.01188 -0.1429 0.7114 1.0000
3.500 0.9964 0.02045 0.01222 -0.1424 0.7027 1.0000
3.750 1.0273 0.02055 0.01230 -0.1427 0.6953 1.0000
4.000 1.0486 0.02107 0.01286 -0.1416 0.6860 1.0000
4.250 1.0818 0.02111 0.01290 -0.1423 0.6794 1.0000
4.500 1.1003 0.02175 0.01362 -0.1408 0.6698 1.0000
4.750 1.1351 0.02177 0.01362 -0.1417 0.6638 1.0000
5.000 1.1512 0.02252 0.01452 -0.1399 0.6540 1.0000
5.250 1.1845 0.02262 0.01463 -0.1406 0.6477 1.0000
5.500 1.2014 0.02334 0.01549 -0.1389 0.6382 1.0000
5.750 1.2292 0.02367 0.01588 -0.1388 0.6309 1.0000
6.000 1.2514 0.02419 0.01653 -0.1379 0.6222 1.0000
6.250 1.2742 0.02472 0.01718 -0.1370 0.6138 1.0000
6.500 1.3029 0.02494 0.01750 -0.1369 0.6057 1.0000
6.750 1.3205 0.02563 0.01836 -0.1352 0.5959 1.0000
7.000 1.3487 0.02560 0.01843 -0.1347 0.5846 1.0000
7.250 1.3755 0.02477 0.01759 -0.1331 0.5639 1.0000
7.500 1.4006 0.02394 0.01669 -0.1312 0.5406 1.0000
7.750 1.4181 0.02377 0.01661 -0.1286 0.5204 1.0000
8.000 1.4383 0.02346 0.01626 -0.1264 0.4984 1.0000
8.250 1.4468 0.02356 0.01649 -0.1225 0.4755 1.0000
8.500 1.4553 0.02363 0.01663 -0.1185 0.4500 1.0000
8.750 1.4565 0.02388 0.01696 -0.1135 0.4190 1.0000
9.000 1.4481 0.02436 0.01742 -0.1069 0.3771 1.0000
9.250 1.4292 0.02561 0.01830 -0.0992 0.3049 1.0000
9.500 1.4017 0.02824 0.02022 -0.0918 0.2150 1.0000
9.750 1.3746 0.03169 0.02305 -0.0858 0.1508 1.0000
10.000 1.3535 0.03519 0.02619 -0.0810 0.1176 1.0000
10.250 1.3387 0.03846 0.02932 -0.0774 0.1014 1.0000
10.500 1.3299 0.04146 0.03233 -0.0745 0.0907 1.0000
10.750 1.3233 0.04441 0.03526 -0.0720 0.0833 1.0000
11.000 1.3222 0.04701 0.03785 -0.0700 0.0764 1.0000
11.250 1.3266 0.04929 0.04013 -0.0680 0.0703 1.0000
11.500 1.3383 0.05111 0.04192 -0.0664 0.0655 1.0000
11.750 1.3726 0.05233 0.04300 -0.0651 0.0607 1.0000
12.000 1.3965 0.05400 0.04487 -0.0642 0.0571 1.0000
12.250 1.4203 0.05589 0.04681 -0.0635 0.0535 1.0000
12.500 1.4911 0.05987 0.05088 -0.0662 0.0506 1.0000
12.750 1.5013 0.06303 0.05441 -0.0646 0.0502 1.0000
13.000 1.5013 0.06619 0.05794 -0.0625 0.0497 1.0000
13.250 1.4964 0.06952 0.06163 -0.0604 0.0492 1.0000
13.500 1.4878 0.07308 0.06553 -0.0584 0.0487 1.0000
13.750 1.4767 0.07697 0.06977 -0.0567 0.0483 1.0000
14.000 1.4639 0.08122 0.07434 -0.0554 0.0482 1.0000
14.250 1.4487 0.08586 0.07928 -0.0546 0.0483 1.0000
14.500 1.4321 0.09091 0.08462 -0.0542 0.0485 1.0000
14.750 1.4136 0.09629 0.09027 -0.0545 0.0489 1.0000
15.000 1.3943 0.10200 0.09622 -0.0553 0.0492 1.0000
15.250 1.3743 0.10807 0.10251 -0.0568 0.0496 1.0000
15.500 1.3547 0.11450 0.10914 -0.0588 0.0500 1.0000
15.750 1.3385 0.12133 0.11614 -0.0612 0.0505 1.0000
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Polar data table (+)
Polar graphs
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