NACA6409 9% (n6409-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA6409 9% (n6409-il) Reynolds number: 200,000 Max Cl/Cd: 87.4 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6409-il-200000-n5.txt Download as CSV file: xf-n6409-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2185 0.10530 0.10173 -0.0605 0.9816 0.0286
-9.000 -0.2076 0.10160 0.09804 -0.0645 0.9768 0.0287
-8.750 -0.1934 0.09740 0.09384 -0.0689 0.9733 0.0287
-8.250 -0.1720 0.08756 0.08398 -0.0742 0.9636 0.0229
-7.750 -0.1381 0.08078 0.07718 -0.0796 0.9565 0.0221
-7.500 -0.1306 0.07697 0.07338 -0.0830 0.9478 0.0222
-7.000 -0.0972 0.06681 0.06320 -0.0969 0.9330 0.0233
-6.500 -0.0542 0.05500 0.05125 -0.1130 0.9174 0.0230
-6.250 -0.0324 0.05010 0.04627 -0.1192 0.9092 0.0233
-6.000 -0.0059 0.04660 0.04267 -0.1241 0.9027 0.0238
-5.750 0.0205 0.04329 0.03925 -0.1284 0.8963 0.0250
-5.500 0.0495 0.03566 0.03131 -0.1363 0.8884 0.0261
-5.250 0.0758 0.02239 0.01663 -0.1445 0.8806 0.0269
-5.000 0.1032 0.01982 0.01343 -0.1454 0.8744 0.0280
-4.750 0.1340 0.01829 0.01154 -0.1465 0.8698 0.0296
-4.500 0.1589 0.01748 0.01058 -0.1461 0.8618 0.0308
-4.250 0.1900 0.01650 0.00937 -0.1468 0.8566 0.0320
-4.000 0.2159 0.01572 0.00840 -0.1465 0.8486 0.0334
-3.750 0.2462 0.01495 0.00742 -0.1469 0.8424 0.0353
-3.500 0.2726 0.01437 0.00675 -0.1466 0.8342 0.0377
-3.250 0.3024 0.01394 0.00623 -0.1469 0.8274 0.0409
-3.000 0.3290 0.01350 0.00568 -0.1466 0.8186 0.0442
-2.750 0.3585 0.01303 0.00514 -0.1468 0.8110 0.0487
-2.500 0.3850 0.01278 0.00481 -0.1464 0.8015 0.0556
-2.250 0.4129 0.01250 0.00451 -0.1464 0.7929 0.0651
-2.000 0.4407 0.01226 0.00424 -0.1463 0.7836 0.0757
-1.750 0.4675 0.01210 0.00406 -0.1460 0.7734 0.0891
-1.500 0.4951 0.01194 0.00387 -0.1458 0.7636 0.1037
-1.250 0.5223 0.01181 0.00371 -0.1456 0.7535 0.1198
-1.000 0.5488 0.01171 0.00360 -0.1453 0.7427 0.1379
-0.750 0.5756 0.01162 0.00349 -0.1450 0.7319 0.1577
-0.500 0.6023 0.01155 0.00342 -0.1447 0.7210 0.1808
-0.250 0.6285 0.01149 0.00337 -0.1443 0.7095 0.2073
0.000 0.6544 0.01145 0.00336 -0.1439 0.6982 0.2372
0.250 0.6804 0.01141 0.00335 -0.1434 0.6870 0.2738
0.500 0.7060 0.01135 0.00335 -0.1430 0.6758 0.3217
0.750 0.7307 0.01117 0.00339 -0.1425 0.6644 0.4133
1.250 0.7890 0.01032 0.00348 -0.1427 0.6426 1.0000
1.500 0.8146 0.01049 0.00352 -0.1422 0.6320 1.0000
1.750 0.8399 0.01065 0.00359 -0.1416 0.6212 1.0000
2.000 0.8652 0.01083 0.00367 -0.1411 0.6112 1.0000
2.250 0.8905 0.01102 0.00377 -0.1406 0.6018 1.0000
2.500 0.9156 0.01120 0.00390 -0.1400 0.5920 1.0000
2.750 0.9408 0.01139 0.00403 -0.1395 0.5833 1.0000
3.000 0.9659 0.01160 0.00418 -0.1389 0.5746 1.0000
3.250 0.9909 0.01180 0.00436 -0.1384 0.5663 1.0000
3.500 1.0159 0.01202 0.00453 -0.1379 0.5586 1.0000
3.750 1.0409 0.01222 0.00474 -0.1373 0.5508 1.0000
4.000 1.0658 0.01246 0.00494 -0.1368 0.5436 1.0000
4.250 1.0905 0.01267 0.00518 -0.1362 0.5363 1.0000
4.500 1.1152 0.01291 0.00541 -0.1357 0.5294 1.0000
4.750 1.1399 0.01314 0.00568 -0.1351 0.5226 1.0000
5.000 1.1643 0.01339 0.00595 -0.1345 0.5159 1.0000
5.250 1.1887 0.01364 0.00623 -0.1339 0.5094 1.0000
5.500 1.2128 0.01389 0.00653 -0.1333 0.5025 1.0000
5.750 1.2369 0.01417 0.00685 -0.1326 0.4961 1.0000
6.000 1.2603 0.01442 0.00719 -0.1319 0.4885 1.0000
6.250 1.2823 0.01470 0.00750 -0.1308 0.4785 1.0000
6.500 1.3006 0.01498 0.00780 -0.1290 0.4609 1.0000
6.750 1.3159 0.01533 0.00808 -0.1267 0.4380 1.0000
7.000 1.3310 0.01567 0.00841 -0.1243 0.4124 1.0000
7.250 1.3443 0.01611 0.00878 -0.1217 0.3827 1.0000
7.500 1.3533 0.01670 0.00922 -0.1184 0.3442 1.0000
7.750 1.3577 0.01750 0.00982 -0.1144 0.3014 1.0000
8.000 1.3578 0.01865 0.01067 -0.1099 0.2497 1.0000
8.250 1.3554 0.02010 0.01180 -0.1054 0.1932 1.0000
8.500 1.3524 0.02174 0.01312 -0.1010 0.1406 1.0000
8.750 1.3515 0.02334 0.01449 -0.0973 0.1007 1.0000
9.000 1.3524 0.02490 0.01590 -0.0939 0.0730 1.0000
9.250 1.3558 0.02635 0.01729 -0.0910 0.0556 1.0000
9.500 1.3603 0.02778 0.01871 -0.0884 0.0449 1.0000
9.750 1.3650 0.02926 0.02023 -0.0859 0.0380 1.0000
10.000 1.3697 0.03079 0.02181 -0.0836 0.0331 1.0000
10.250 1.3737 0.03244 0.02354 -0.0814 0.0302 1.0000
10.500 1.3788 0.03407 0.02529 -0.0794 0.0281 1.0000
10.750 1.3824 0.03590 0.02721 -0.0775 0.0264 1.0000
11.000 1.3834 0.03802 0.02941 -0.0756 0.0250 1.0000
11.250 1.3841 0.04026 0.03175 -0.0739 0.0239 1.0000
11.500 1.3869 0.04240 0.03405 -0.0725 0.0230 1.0000
11.750 1.3894 0.04464 0.03640 -0.0712 0.0220 1.0000
12.000 1.3912 0.04701 0.03888 -0.0701 0.0211 1.0000
12.250 1.3927 0.04951 0.04148 -0.0691 0.0203 1.0000
12.500 1.3928 0.05225 0.04432 -0.0682 0.0198 1.0000
12.750 1.3913 0.05526 0.04741 -0.0674 0.0192 1.0000
13.000 1.3889 0.05844 0.05066 -0.0667 0.0188 1.0000
13.250 1.3914 0.06113 0.05348 -0.0661 0.0185 1.0000
13.500 1.3941 0.06385 0.05634 -0.0656 0.0181 1.0000
13.750 1.3970 0.06657 0.05919 -0.0651 0.0177 1.0000
14.000 1.4003 0.06929 0.06204 -0.0647 0.0172 1.0000
14.250 1.4038 0.07204 0.06491 -0.0644 0.0167 1.0000
14.500 1.4070 0.07486 0.06785 -0.0643 0.0162 1.0000
14.750 1.4098 0.07778 0.07087 -0.0643 0.0157 1.0000
15.000 1.4121 0.08080 0.07399 -0.0644 0.0152 1.0000
15.250 1.4147 0.08380 0.07708 -0.0644 0.0149 1.0000
15.500 1.4172 0.08682 0.08019 -0.0644 0.0146 1.0000
15.750 1.4203 0.08978 0.08326 -0.0642 0.0143 1.0000
16.000 1.4215 0.09318 0.08686 -0.0645 0.0141 1.0000
16.250 1.4213 0.09689 0.09079 -0.0651 0.0139 1.0000
16.500 1.4194 0.10091 0.09503 -0.0659 0.0136 1.0000
16.750 1.4161 0.10523 0.09957 -0.0671 0.0133 1.0000
17.000 1.4114 0.10984 0.10440 -0.0686 0.0130 1.0000
17.250 1.4057 0.11471 0.10947 -0.0704 0.0128 1.0000
17.500 1.3993 0.11979 0.11476 -0.0725 0.0125 1.0000
17.750 1.3918 0.12520 0.12035 -0.0749 0.0123 1.0000
18.000 1.3835 0.13085 0.12620 -0.0778 0.0121 1.0000
18.250 1.3739 0.13693 0.13248 -0.0810 0.0120 1.0000
18.500 1.3633 0.14339 0.13913 -0.0846 0.0118 1.0000
18.750 1.3513 0.15039 0.14633 -0.0888 0.0118 1.0000
19.000 1.3376 0.15808 0.15422 -0.0936 0.0117 1.0000
19.250 1.3209 0.16694 0.16329 -0.0994 0.0117 1.0000
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Polar data table (+)
Polar graphs
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