NACA6409 9% (n6409-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA6409 9% (n6409-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.99 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6409-il-1000000.txt Download as CSV file: xf-n6409-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1128 0.08228 0.08057 -0.0891 0.9737 0.0150
-8.500 -0.0962 0.07788 0.07617 -0.0942 0.9717 0.0150
-7.500 -0.0938 0.01913 0.01606 -0.1571 0.9150 0.0148
-7.250 -0.0768 0.01594 0.01235 -0.1573 0.9070 0.0153
-7.000 -0.0537 0.01425 0.01038 -0.1574 0.9007 0.0159
-6.750 -0.0287 0.01365 0.00969 -0.1571 0.8943 0.0164
-6.500 -0.0027 0.01308 0.00900 -0.1570 0.8882 0.0169
-6.250 0.0232 0.01248 0.00825 -0.1568 0.8819 0.0176
-6.000 0.0494 0.01206 0.00771 -0.1565 0.8749 0.0183
-5.750 0.0759 0.01160 0.00710 -0.1563 0.8684 0.0188
-5.500 0.1024 0.01126 0.00664 -0.1560 0.8611 0.0191
-5.250 0.1265 0.00988 0.00501 -0.1556 0.8544 0.0201
-5.000 0.1527 0.00949 0.00456 -0.1553 0.8467 0.0209
-4.750 0.1795 0.00920 0.00419 -0.1550 0.8394 0.0218
-4.500 0.2061 0.00895 0.00387 -0.1547 0.8310 0.0228
-4.250 0.2329 0.00872 0.00356 -0.1544 0.8233 0.0236
-4.000 0.2596 0.00851 0.00326 -0.1541 0.8148 0.0241
-3.750 0.2855 0.00800 0.00265 -0.1537 0.8065 0.0257
-3.500 0.3120 0.00781 0.00240 -0.1534 0.7975 0.0273
-3.250 0.3388 0.00766 0.00220 -0.1531 0.7878 0.0290
-3.000 0.3655 0.00757 0.00204 -0.1527 0.7784 0.0307
-2.750 0.3917 0.00736 0.00178 -0.1523 0.7685 0.0353
-2.500 0.4184 0.00723 0.00162 -0.1520 0.7585 0.0410
-2.250 0.4448 0.00716 0.00152 -0.1516 0.7481 0.0488
-2.000 0.4709 0.00710 0.00144 -0.1512 0.7370 0.0585
-1.750 0.4972 0.00704 0.00137 -0.1508 0.7254 0.0692
-1.500 0.5236 0.00700 0.00132 -0.1504 0.7141 0.0800
-1.250 0.5497 0.00698 0.00127 -0.1500 0.7025 0.0918
-1.000 0.5756 0.00697 0.00125 -0.1496 0.6904 0.1065
-0.750 0.6014 0.00697 0.00124 -0.1491 0.6777 0.1245
-0.500 0.6273 0.00698 0.00124 -0.1487 0.6649 0.1449
-0.250 0.6532 0.00697 0.00126 -0.1483 0.6522 0.1678
0.000 0.6790 0.00700 0.00128 -0.1479 0.6394 0.1905
0.250 0.7047 0.00702 0.00132 -0.1474 0.6267 0.2167
0.500 0.7302 0.00705 0.00136 -0.1470 0.6144 0.2467
0.750 0.7556 0.00709 0.00142 -0.1465 0.6020 0.2795
1.000 0.7810 0.00710 0.00149 -0.1460 0.5899 0.3263
1.250 0.8058 0.00693 0.00158 -0.1456 0.5787 0.4537
1.500 0.8374 0.00603 0.00179 -0.1467 0.5679 1.0000
1.750 0.8626 0.00617 0.00185 -0.1461 0.5577 1.0000
2.000 0.8884 0.00629 0.00192 -0.1457 0.5478 1.0000
2.250 0.9141 0.00642 0.00199 -0.1452 0.5392 1.0000
2.500 0.9394 0.00656 0.00208 -0.1447 0.5305 1.0000
2.750 0.9653 0.00667 0.00216 -0.1443 0.5230 1.0000
3.000 0.9905 0.00682 0.00226 -0.1438 0.5154 1.0000
3.250 1.0165 0.00693 0.00236 -0.1435 0.5088 1.0000
3.500 1.0418 0.00707 0.00247 -0.1430 0.5020 1.0000
3.750 1.0673 0.00720 0.00258 -0.1426 0.4960 1.0000
4.000 1.0930 0.00733 0.00270 -0.1421 0.4899 1.0000
4.250 1.1176 0.00750 0.00284 -0.1416 0.4837 1.0000
4.500 1.1436 0.00760 0.00295 -0.1412 0.4780 1.0000
4.750 1.1678 0.00778 0.00311 -0.1406 0.4701 1.0000
5.000 1.1928 0.00790 0.00323 -0.1401 0.4601 1.0000
5.250 1.2157 0.00813 0.00338 -0.1392 0.4421 1.0000
5.500 1.2384 0.00837 0.00354 -0.1382 0.4243 1.0000
5.750 1.2619 0.00857 0.00371 -0.1375 0.4099 1.0000
6.000 1.2848 0.00880 0.00390 -0.1366 0.3940 1.0000
6.250 1.3071 0.00905 0.00410 -0.1356 0.3749 1.0000
6.500 1.3272 0.00943 0.00436 -0.1343 0.3492 1.0000
6.750 1.3446 0.00995 0.00472 -0.1325 0.3123 1.0000
7.000 1.3575 0.01074 0.00523 -0.1299 0.2632 1.0000
7.250 1.3652 0.01174 0.00589 -0.1264 0.2029 1.0000
7.500 1.3682 0.01286 0.00666 -0.1221 0.1421 1.0000
7.750 1.3721 0.01394 0.00744 -0.1179 0.0927 1.0000
8.000 1.3795 0.01484 0.00816 -0.1145 0.0613 1.0000
8.250 1.3899 0.01559 0.00881 -0.1117 0.0428 1.0000
8.500 1.4009 0.01632 0.00947 -0.1090 0.0296 1.0000
8.750 1.4131 0.01700 0.01013 -0.1065 0.0232 1.0000
9.000 1.4243 0.01774 0.01087 -0.1040 0.0195 1.0000
9.250 1.4382 0.01835 0.01153 -0.1019 0.0182 1.0000
9.500 1.4515 0.01899 0.01221 -0.0998 0.0170 1.0000
9.750 1.4633 0.01975 0.01300 -0.0976 0.0160 1.0000
10.000 1.4709 0.02077 0.01408 -0.0948 0.0148 1.0000
10.250 1.4809 0.02168 0.01506 -0.0925 0.0142 1.0000
10.500 1.4921 0.02254 0.01598 -0.0905 0.0139 1.0000
10.750 1.5026 0.02346 0.01697 -0.0885 0.0134 1.0000
11.000 1.5116 0.02453 0.01810 -0.0864 0.0130 1.0000
11.250 1.5200 0.02567 0.01930 -0.0843 0.0125 1.0000
11.500 1.5275 0.02691 0.02060 -0.0823 0.0122 1.0000
11.750 1.5328 0.02838 0.02212 -0.0802 0.0118 1.0000
12.000 1.5346 0.03018 0.02400 -0.0779 0.0114 1.0000
12.250 1.5279 0.03277 0.02672 -0.0751 0.0109 1.0000
12.500 1.5299 0.03478 0.02883 -0.0733 0.0108 1.0000
12.750 1.5365 0.03642 0.03054 -0.0720 0.0106 1.0000
13.000 1.5418 0.03824 0.03244 -0.0707 0.0104 1.0000
13.250 1.5450 0.04035 0.03463 -0.0695 0.0103 1.0000
13.500 1.5482 0.04253 0.03690 -0.0684 0.0101 1.0000
13.750 1.5501 0.04492 0.03938 -0.0674 0.0099 1.0000
14.000 1.5532 0.04726 0.04180 -0.0665 0.0096 1.0000
14.250 1.5568 0.04962 0.04423 -0.0659 0.0094 1.0000
14.500 1.5584 0.05228 0.04698 -0.0653 0.0092 1.0000
14.750 1.5603 0.05495 0.04972 -0.0649 0.0089 1.0000
15.000 1.5608 0.05789 0.05273 -0.0646 0.0088 1.0000
15.250 1.5595 0.06111 0.05603 -0.0645 0.0085 1.0000
15.500 1.5544 0.06492 0.05993 -0.0644 0.0083 1.0000
15.750 1.5449 0.06932 0.06444 -0.0643 0.0081 1.0000
16.000 1.5378 0.07352 0.06877 -0.0643 0.0079 1.0000
16.250 1.5390 0.07678 0.07213 -0.0647 0.0079 1.0000
16.500 1.5403 0.08008 0.07553 -0.0653 0.0078 1.0000
16.750 1.5408 0.08353 0.07908 -0.0659 0.0077 1.0000
17.000 1.5398 0.08725 0.08291 -0.0666 0.0076 1.0000
17.250 1.5386 0.09107 0.08683 -0.0675 0.0074 1.0000
17.500 1.5368 0.09504 0.09091 -0.0685 0.0073 1.0000
17.750 1.5344 0.09916 0.09514 -0.0696 0.0072 1.0000
18.000 1.5319 0.10337 0.09945 -0.0710 0.0070 1.0000
18.250 1.5286 0.10774 0.10393 -0.0725 0.0069 1.0000
18.500 1.5254 0.11216 0.10845 -0.0741 0.0068 1.0000
18.750 1.5229 0.11655 0.11293 -0.0759 0.0066 1.0000
19.000 1.5201 0.12102 0.11749 -0.0778 0.0065 1.0000
19.250 1.5156 0.12579 0.12236 -0.0799 0.0064 1.0000
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Polar data table (+)
Polar graphs
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