NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 50,000 Max Cl/Cd: 22.01 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nplx-il-50000.txt Download as CSV file: xf-nplx-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NPL AIRFOIL FROM ARC CP 1372
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4425 0.10052 0.09294 0.0019 1.0000 0.4414
-7.750 -0.4374 0.09722 0.08967 0.0024 1.0000 0.4522
-7.500 -0.4383 0.09381 0.08632 0.0022 1.0000 0.4519
-7.000 -0.6699 0.06197 0.05445 -0.0345 1.0000 0.1621
-6.750 -0.6745 0.05679 0.04881 -0.0345 1.0000 0.1461
-6.500 -0.6737 0.05256 0.04390 -0.0336 1.0000 0.1355
-6.250 -0.6628 0.04890 0.03997 -0.0325 1.0000 0.1338
-6.000 -0.6504 0.04554 0.03626 -0.0313 1.0000 0.1326
-5.750 -0.6357 0.04232 0.03262 -0.0300 1.0000 0.1317
-5.500 -0.6183 0.03941 0.02929 -0.0287 1.0000 0.1318
-5.250 -0.5994 0.03703 0.02642 -0.0273 1.0000 0.1355
-5.000 -0.5785 0.03456 0.02355 -0.0260 1.0000 0.1387
-4.750 -0.5568 0.03226 0.02126 -0.0249 1.0000 0.1462
-4.500 -0.5338 0.03057 0.01917 -0.0235 1.0000 0.1534
-4.250 -0.5105 0.02863 0.01738 -0.0221 1.0000 0.1639
-4.000 -0.4873 0.02704 0.01584 -0.0203 1.0000 0.1762
-3.750 -0.4660 0.02565 0.01453 -0.0183 1.0000 0.1923
-3.500 -0.4473 0.02426 0.01328 -0.0161 1.0000 0.2130
-3.250 -0.4311 0.02249 0.01186 -0.0144 1.0000 0.2479
-3.000 -0.4261 0.02009 0.01175 -0.0104 1.0000 0.5128
-2.750 -0.4340 0.02267 0.01464 0.0033 1.0000 0.6819
-2.500 -0.4383 0.02432 0.01630 0.0154 1.0000 0.7398
-2.250 -0.4362 0.02511 0.01699 0.0244 1.0000 0.7816
-2.000 -0.1922 0.02883 0.01952 0.0044 1.0000 0.9333
-1.750 -0.1737 0.02819 0.01879 0.0047 1.0000 0.9401
-1.500 -0.1679 0.02764 0.01820 0.0071 1.0000 0.9440
-1.250 -0.1480 0.02700 0.01749 0.0070 1.0000 0.9477
-1.000 -0.1319 0.02646 0.01690 0.0075 1.0000 0.9524
-0.750 -0.1231 0.02601 0.01643 0.0093 1.0000 0.9574
-0.500 -0.1001 0.02550 0.01587 0.0085 1.0000 0.9620
-0.250 -0.0791 0.02507 0.01542 0.0080 1.0000 0.9678
0.000 -0.0568 0.02469 0.01501 0.0073 1.0000 0.9738
0.250 -0.0310 0.02433 0.01465 0.0058 1.0000 0.9800
0.500 -0.0021 0.02402 0.01435 0.0037 1.0000 0.9871
0.750 0.0284 0.02378 0.01412 0.0013 1.0000 0.9950
1.000 0.0471 0.02358 0.01396 0.0008 1.0000 1.0000
1.250 0.0442 0.02336 0.01379 0.0041 1.0000 1.0000
1.500 0.0398 0.02308 0.01357 0.0075 1.0000 1.0000
1.750 0.0335 0.02274 0.01328 0.0111 1.0000 1.0000
2.000 0.0253 0.02232 0.01291 0.0149 1.0000 1.0000
2.250 0.0177 0.02186 0.01250 0.0184 1.0000 1.0000
2.500 0.0219 0.02164 0.01230 0.0200 1.0000 1.0000
2.750 0.0382 0.02173 0.01242 0.0195 1.0000 1.0000
3.000 0.0595 0.02203 0.01276 0.0182 1.0000 1.0000
3.250 0.0823 0.02249 0.01326 0.0167 1.0000 1.0000
3.500 0.1049 0.02308 0.01392 0.0153 1.0000 1.0000
3.750 0.1263 0.02380 0.01472 0.0139 1.0000 1.0000
4.000 0.1655 0.02510 0.01619 0.0090 0.9900 1.0000
4.250 0.4288 0.02232 0.01481 -0.0204 0.8317 1.0000
4.500 0.4861 0.02209 0.01161 -0.0128 0.2715 1.0000
4.750 0.5066 0.02361 0.01266 -0.0119 0.2254 1.0000
5.000 0.5384 0.02505 0.01383 -0.0127 0.1977 1.0000
5.250 0.5769 0.02668 0.01533 -0.0142 0.1824 1.0000
5.500 0.6136 0.02856 0.01703 -0.0157 0.1720 1.0000
5.750 0.6433 0.03011 0.01880 -0.0159 0.1635 1.0000
6.000 0.6741 0.03227 0.02085 -0.0166 0.1573 1.0000
6.250 0.7013 0.03436 0.02329 -0.0163 0.1553 1.0000
6.500 0.7264 0.03672 0.02604 -0.0158 0.1542 1.0000
6.750 0.7487 0.03923 0.02895 -0.0150 0.1532 1.0000
7.000 0.7680 0.04186 0.03198 -0.0139 0.1515 1.0000
7.250 0.7849 0.04478 0.03529 -0.0128 0.1508 1.0000
7.500 0.7997 0.04824 0.03917 -0.0116 0.1530 1.0000
7.750 0.8156 0.05207 0.04322 -0.0108 0.1558 1.0000
8.000 0.8116 0.05700 0.04900 -0.0090 0.1656 1.0000
8.250 0.8141 0.06215 0.05454 -0.0084 0.1758 1.0000
8.500 0.7882 0.06998 0.06290 -0.0093 0.1974 1.0000
8.750 0.5916 0.09731 0.09026 -0.0426 0.4286 1.0000
9.000 0.5954 0.10067 0.09359 -0.0425 0.4139 1.0000
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Polar data table (+)
Polar graphs
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