NACA6409 9% (n6409-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA6409 9% (n6409-il) Reynolds number: 100,000 Max Cl/Cd: 63.71 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6409-il-100000-n5.txt Download as CSV file: xf-n6409-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2406 0.10188 0.09719 -0.0477 0.9816 0.0527
-7.750 -0.2333 0.09956 0.09489 -0.0545 0.9733 0.0552
-7.500 -0.2275 0.09698 0.09234 -0.0616 0.9624 0.0558
-7.250 -0.2087 0.09270 0.08804 -0.0691 0.9551 0.0559
-7.000 -0.1917 0.08852 0.08384 -0.0742 0.9476 0.0560
-6.750 -0.1678 0.08359 0.07885 -0.0804 0.9432 0.0560
-6.500 -0.1633 0.07847 0.07373 -0.0753 0.9370 0.0442
-6.250 -0.1436 0.07454 0.06978 -0.0778 0.9318 0.0420
-6.000 -0.1255 0.07042 0.06562 -0.0830 0.9232 0.0422
-5.750 -0.0983 0.06553 0.06066 -0.0904 0.9168 0.0423
-5.500 -0.0772 0.06110 0.05615 -0.0955 0.9081 0.0413
-5.250 -0.0445 0.05539 0.05029 -0.1036 0.9023 0.0401
-5.000 -0.0155 0.04985 0.04456 -0.1102 0.8946 0.0394
-4.750 0.0204 0.04445 0.03888 -0.1171 0.8888 0.0405
-4.500 0.0651 0.03726 0.03117 -0.1258 0.8857 0.0422
-4.250 0.0916 0.03205 0.02535 -0.1287 0.8771 0.0426
-4.000 0.1298 0.02747 0.01991 -0.1325 0.8732 0.0438
-3.750 0.1622 0.02531 0.01728 -0.1340 0.8681 0.0466
-3.500 0.1898 0.02427 0.01606 -0.1342 0.8608 0.0494
-3.250 0.2259 0.02258 0.01394 -0.1358 0.8570 0.0524
-3.000 0.2524 0.02143 0.01242 -0.1354 0.8489 0.0555
-2.750 0.2853 0.02059 0.01154 -0.1364 0.8436 0.0611
-2.500 0.3145 0.01984 0.01054 -0.1365 0.8365 0.0679
-2.250 0.3449 0.01918 0.00989 -0.1369 0.8297 0.0765
-2.000 0.3754 0.01862 0.00927 -0.1372 0.8229 0.0880
-1.750 0.4046 0.01818 0.00877 -0.1373 0.8150 0.1023
-1.500 0.4343 0.01778 0.00834 -0.1375 0.8074 0.1192
-1.250 0.4643 0.01739 0.00793 -0.1377 0.7995 0.1384
-1.000 0.4925 0.01709 0.00764 -0.1377 0.7906 0.1590
-0.750 0.5240 0.01676 0.00731 -0.1381 0.7831 0.1859
-0.500 0.5501 0.01657 0.00716 -0.1377 0.7729 0.2135
-0.250 0.5817 0.01630 0.00691 -0.1382 0.7648 0.2509
0.000 0.6102 0.01609 0.00676 -0.1382 0.7550 0.2961
0.250 0.6383 0.01582 0.00665 -0.1382 0.7451 0.3638
0.500 0.6737 0.01438 0.00645 -0.1393 0.7373 1.0000
0.750 0.6997 0.01450 0.00639 -0.1387 0.7259 1.0000
1.000 0.7274 0.01460 0.00633 -0.1385 0.7157 1.0000
1.250 0.7570 0.01468 0.00623 -0.1387 0.7065 1.0000
1.500 0.7831 0.01483 0.00627 -0.1382 0.6956 1.0000
1.750 0.8099 0.01498 0.00632 -0.1379 0.6853 1.0000
2.000 0.8383 0.01512 0.00632 -0.1379 0.6761 1.0000
2.250 0.8641 0.01531 0.00646 -0.1374 0.6658 1.0000
2.500 0.8903 0.01551 0.00659 -0.1370 0.6560 1.0000
3.000 0.9430 0.01594 0.00691 -0.1363 0.6375 1.0000
3.250 0.9694 0.01617 0.00709 -0.1360 0.6289 1.0000
3.500 0.9953 0.01641 0.00730 -0.1356 0.6202 1.0000
3.750 1.0205 0.01668 0.00757 -0.1351 0.6115 1.0000
4.000 1.0471 0.01694 0.00781 -0.1349 0.6037 1.0000
4.250 1.0712 0.01725 0.00816 -0.1342 0.5952 1.0000
4.500 1.0981 0.01752 0.00841 -0.1340 0.5880 1.0000
4.750 1.1214 0.01786 0.00885 -0.1332 0.5796 1.0000
5.000 1.1482 0.01815 0.00913 -0.1330 0.5728 1.0000
5.250 1.1708 0.01852 0.00961 -0.1322 0.5645 1.0000
5.500 1.1974 0.01883 0.00993 -0.1319 0.5578 1.0000
5.750 1.2194 0.01923 0.01048 -0.1310 0.5495 1.0000
6.000 1.2456 0.01955 0.01085 -0.1306 0.5428 1.0000
6.250 1.2669 0.01997 0.01142 -0.1296 0.5344 1.0000
6.500 1.2929 0.02031 0.01180 -0.1292 0.5274 1.0000
6.750 1.3129 0.02075 0.01245 -0.1279 0.5183 1.0000
7.000 1.3345 0.02109 0.01290 -0.1267 0.5079 1.0000
7.250 1.3499 0.02133 0.01318 -0.1243 0.4887 1.0000
7.500 1.3622 0.02156 0.01338 -0.1212 0.4646 1.0000
7.750 1.3721 0.02191 0.01377 -0.1179 0.4393 1.0000
8.000 1.3818 0.02236 0.01428 -0.1147 0.4152 1.0000
8.250 1.3881 0.02289 0.01482 -0.1110 0.3860 1.0000
8.500 1.3900 0.02360 0.01543 -0.1066 0.3489 1.0000
8.750 1.3885 0.02466 0.01627 -0.1020 0.3006 1.0000
9.000 1.3808 0.02629 0.01753 -0.0970 0.2433 1.0000
9.250 1.3688 0.02850 0.01933 -0.0921 0.1831 1.0000
9.500 1.3573 0.03100 0.02148 -0.0878 0.1330 1.0000
9.750 1.3481 0.03353 0.02380 -0.0842 0.0985 1.0000
10.000 1.3421 0.03598 0.02614 -0.0812 0.0770 1.0000
10.250 1.3381 0.03840 0.02853 -0.0786 0.0643 1.0000
10.500 1.3355 0.04084 0.03102 -0.0763 0.0565 1.0000
10.750 1.3321 0.04346 0.03370 -0.0743 0.0513 1.0000
11.000 1.3293 0.04615 0.03649 -0.0726 0.0476 1.0000
11.250 1.3279 0.04881 0.03930 -0.0711 0.0443 1.0000
11.500 1.3252 0.05169 0.04228 -0.0699 0.0416 1.0000
11.750 1.3205 0.05489 0.04553 -0.0687 0.0396 1.0000
12.000 1.3219 0.05755 0.04836 -0.0678 0.0373 1.0000
12.250 1.3225 0.06034 0.05131 -0.0670 0.0355 1.0000
12.500 1.3235 0.06315 0.05423 -0.0662 0.0341 1.0000
12.750 1.3250 0.06594 0.05709 -0.0655 0.0328 1.0000
13.000 1.3274 0.06863 0.05983 -0.0647 0.0318 1.0000
13.250 1.3346 0.07083 0.06210 -0.0637 0.0308 1.0000
13.500 1.3433 0.07296 0.06441 -0.0628 0.0296 1.0000
13.750 1.3510 0.07526 0.06687 -0.0621 0.0283 1.0000
14.000 1.3572 0.07776 0.06954 -0.0617 0.0271 1.0000
14.250 1.3635 0.08030 0.07219 -0.0612 0.0261 1.0000
14.500 1.3711 0.08276 0.07476 -0.0607 0.0254 1.0000
14.750 1.3801 0.08518 0.07726 -0.0601 0.0247 1.0000
15.000 1.3881 0.08800 0.08024 -0.0595 0.0242 1.0000
15.250 1.3890 0.09165 0.08419 -0.0595 0.0238 1.0000
15.500 1.3861 0.09583 0.08868 -0.0600 0.0234 1.0000
15.750 1.3802 0.10045 0.09359 -0.0610 0.0230 1.0000
16.000 1.3721 0.10545 0.09887 -0.0624 0.0226 1.0000
16.250 1.3623 0.11082 0.10452 -0.0642 0.0222 1.0000
16.500 1.3511 0.11656 0.11051 -0.0666 0.0219 1.0000
16.750 1.3387 0.12272 0.11692 -0.0694 0.0217 1.0000
17.000 1.3246 0.12943 0.12387 -0.0729 0.0215 1.0000
17.250 1.3086 0.13686 0.13154 -0.0771 0.0215 1.0000
17.500 1.2903 0.14518 0.14009 -0.0822 0.0215 1.0000
17.750 1.2691 0.15482 0.14996 -0.0885 0.0217 1.0000
18.000 1.2442 0.16640 0.16174 -0.0963 0.0221 1.0000
18.250 1.2160 0.18055 0.17603 -0.1059 0.0227 1.0000
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