N-9 (n9-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 100,000 Max Cl/Cd: 51.57 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n9-il-100000-n5.txt Download as CSV file: xf-n9-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4632 0.09003 0.08507 -0.0218 1.0000 0.0308
-9.500 -0.4652 0.08580 0.08091 -0.0240 1.0000 0.0305
-9.250 -0.4692 0.08141 0.07660 -0.0266 1.0000 0.0301
-9.000 -0.4702 0.07614 0.07138 -0.0310 1.0000 0.0296
-8.750 -0.4699 0.07021 0.06547 -0.0360 1.0000 0.0291
-8.500 -0.4686 0.06361 0.05881 -0.0409 1.0000 0.0286
-8.250 -0.4656 0.05689 0.05196 -0.0446 1.0000 0.0284
-8.000 -0.4604 0.05030 0.04514 -0.0471 1.0000 0.0284
-7.750 -0.4515 0.04500 0.03954 -0.0482 1.0000 0.0289
-7.500 -0.4392 0.04088 0.03510 -0.0485 1.0000 0.0306
-7.250 -0.4257 0.03614 0.02982 -0.0486 1.0000 0.0324
-7.000 -0.4095 0.03160 0.02457 -0.0482 1.0000 0.0338
-6.750 -0.3900 0.02822 0.02043 -0.0474 1.0000 0.0353
-6.500 -0.3709 0.02674 0.01889 -0.0467 1.0000 0.0381
-6.250 -0.3498 0.02538 0.01728 -0.0458 1.0000 0.0413
-6.000 -0.3270 0.02351 0.01497 -0.0450 1.0000 0.0442
-5.750 -0.3044 0.02224 0.01347 -0.0442 1.0000 0.0483
-5.500 -0.2819 0.02142 0.01255 -0.0435 1.0000 0.0520
-5.250 -0.2525 0.02046 0.01130 -0.0438 0.9979 0.0572
-5.000 -0.2160 0.01952 0.01031 -0.0458 0.9929 0.0626
-4.750 -0.1792 0.01867 0.00934 -0.0477 0.9873 0.0680
-4.500 -0.1436 0.01802 0.00863 -0.0494 0.9805 0.0760
-4.250 -0.1073 0.01737 0.00785 -0.0511 0.9740 0.0847
-4.000 -0.0716 0.01666 0.00716 -0.0529 0.9669 0.0966
-3.750 -0.0368 0.01606 0.00653 -0.0544 0.9587 0.1133
-3.500 0.0009 0.01541 0.00606 -0.0567 0.9527 0.1424
-3.250 0.0351 0.01489 0.00584 -0.0582 0.9439 0.2062
-3.000 0.0711 0.01410 0.00556 -0.0602 0.9371 0.3291
-2.750 0.1035 0.01317 0.00543 -0.0611 0.9279 0.5504
-2.500 0.1321 0.01232 0.00536 -0.0599 0.9178 0.7913
-2.250 0.1914 0.01195 0.00499 -0.0654 0.9085 1.0000
-2.000 0.2260 0.01191 0.00475 -0.0664 0.8918 1.0000
-1.750 0.2572 0.01189 0.00455 -0.0667 0.8731 1.0000
-1.500 0.2866 0.01190 0.00441 -0.0667 0.8553 1.0000
-1.250 0.3144 0.01194 0.00433 -0.0664 0.8387 1.0000
-1.000 0.3410 0.01200 0.00428 -0.0660 0.8212 1.0000
-0.750 0.3681 0.01204 0.00423 -0.0656 0.8042 1.0000
-0.500 0.3956 0.01209 0.00418 -0.0653 0.7877 1.0000
-0.250 0.4234 0.01214 0.00413 -0.0650 0.7715 1.0000
0.000 0.4511 0.01220 0.00410 -0.0646 0.7557 1.0000
0.250 0.4786 0.01229 0.00409 -0.0643 0.7398 1.0000
0.500 0.5058 0.01242 0.00413 -0.0639 0.7239 1.0000
0.750 0.5325 0.01257 0.00421 -0.0634 0.7070 1.0000
1.000 0.5585 0.01275 0.00431 -0.0628 0.6872 1.0000
1.250 0.5842 0.01294 0.00442 -0.0621 0.6650 1.0000
1.500 0.6093 0.01313 0.00455 -0.0614 0.6400 1.0000
1.750 0.6343 0.01334 0.00469 -0.0606 0.6142 1.0000
2.000 0.6593 0.01354 0.00485 -0.0599 0.5877 1.0000
2.250 0.6840 0.01376 0.00502 -0.0592 0.5563 1.0000
2.500 0.7084 0.01401 0.00518 -0.0584 0.5209 1.0000
2.750 0.7327 0.01431 0.00539 -0.0576 0.4874 1.0000
3.000 0.7565 0.01468 0.00562 -0.0568 0.4539 1.0000
3.250 0.7798 0.01512 0.00591 -0.0560 0.4199 1.0000
3.500 0.8032 0.01559 0.00628 -0.0553 0.3915 1.0000
3.750 0.8264 0.01608 0.00668 -0.0546 0.3647 1.0000
4.000 0.8500 0.01656 0.00712 -0.0539 0.3405 1.0000
4.250 0.8734 0.01704 0.00759 -0.0533 0.3152 1.0000
4.500 0.8962 0.01757 0.00811 -0.0526 0.2836 1.0000
4.750 0.9185 0.01816 0.00862 -0.0518 0.2412 1.0000
5.000 0.9391 0.01895 0.00920 -0.0509 0.1905 1.0000
5.250 0.9592 0.01988 0.00991 -0.0500 0.1598 1.0000
5.500 0.9796 0.02077 0.01076 -0.0491 0.1447 1.0000
6.000 1.0205 0.02251 0.01257 -0.0472 0.1287 1.0000
6.250 1.0397 0.02350 0.01359 -0.0461 0.1224 1.0000
6.500 1.0597 0.02443 0.01463 -0.0451 0.1167 1.0000
6.750 1.0798 0.02538 0.01574 -0.0442 0.1113 1.0000
7.000 1.0980 0.02664 0.01696 -0.0431 0.1056 1.0000
7.250 1.1179 0.02735 0.01792 -0.0423 0.0960 1.0000
7.500 1.1361 0.02817 0.01889 -0.0414 0.0863 1.0000
7.750 1.1534 0.02897 0.01977 -0.0404 0.0774 1.0000
8.000 1.1730 0.02957 0.02065 -0.0396 0.0672 1.0000
8.250 1.1908 0.03037 0.02164 -0.0385 0.0562 1.0000
8.500 1.2060 0.03140 0.02279 -0.0373 0.0450 1.0000
8.750 1.2172 0.03286 0.02429 -0.0355 0.0372 1.0000
9.000 1.2248 0.03455 0.02599 -0.0334 0.0329 1.0000
9.250 1.2314 0.03623 0.02787 -0.0311 0.0294 1.0000
9.500 1.2356 0.03794 0.02968 -0.0289 0.0269 1.0000
9.750 1.2373 0.04002 0.03187 -0.0266 0.0252 1.0000
10.000 1.2398 0.04222 0.03430 -0.0246 0.0239 1.0000
10.250 1.2407 0.04464 0.03694 -0.0229 0.0228 1.0000
10.500 1.2403 0.04727 0.03978 -0.0214 0.0220 1.0000
10.750 1.2384 0.05010 0.04281 -0.0203 0.0213 1.0000
11.000 1.2349 0.05318 0.04608 -0.0197 0.0206 1.0000
11.250 1.2294 0.05662 0.04968 -0.0195 0.0199 1.0000
11.500 1.2220 0.06051 0.05374 -0.0198 0.0195 1.0000
11.750 1.2120 0.06496 0.05836 -0.0206 0.0190 1.0000
12.000 1.2005 0.06991 0.06350 -0.0219 0.0187 1.0000
12.250 1.1883 0.07526 0.06910 -0.0237 0.0185 1.0000
12.500 1.1740 0.08124 0.07533 -0.0263 0.0184 1.0000
12.750 1.1580 0.08786 0.08217 -0.0295 0.0184 1.0000
13.000 1.1401 0.09520 0.08972 -0.0333 0.0184 1.0000
13.250 1.1212 0.10325 0.09795 -0.0378 0.0185 1.0000
13.500 1.1015 0.11194 0.10680 -0.0427 0.0186 1.0000
13.750 1.0809 0.12124 0.11624 -0.0479 0.0188 1.0000
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Polar data table (+)
Polar graphs
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