NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 100,000 Max Cl/Cd: 23.3 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9510-il-100000-n5.txt Download as CSV file: xf-npl9510-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9510 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8382 0.10932 0.10313 -0.0263 1.0000 0.0403
-14.500 -0.8914 0.09384 0.08740 -0.0362 1.0000 0.0398
-14.250 -0.9246 0.08425 0.07757 -0.0422 1.0000 0.0396
-14.000 -0.9494 0.07697 0.07005 -0.0464 1.0000 0.0396
-13.750 -0.9684 0.07100 0.06385 -0.0495 1.0000 0.0397
-13.500 -0.9828 0.06593 0.05854 -0.0518 1.0000 0.0399
-13.250 -0.9934 0.06154 0.05391 -0.0535 1.0000 0.0402
-13.000 -1.0006 0.05769 0.04981 -0.0546 1.0000 0.0406
-12.750 -1.0048 0.05428 0.04614 -0.0553 1.0000 0.0410
-12.500 -1.0038 0.05147 0.04316 -0.0555 1.0000 0.0415
-12.250 -0.9968 0.04941 0.04107 -0.0551 1.0000 0.0422
-12.000 -0.9909 0.04741 0.03903 -0.0549 1.0000 0.0431
-11.750 -0.9858 0.04544 0.03697 -0.0545 1.0000 0.0441
-11.500 -0.9810 0.04352 0.03491 -0.0539 1.0000 0.0453
-11.250 -0.9759 0.04170 0.03295 -0.0529 1.0000 0.0465
-11.000 -0.9702 0.04000 0.03107 -0.0516 1.0000 0.0477
-10.750 -0.9617 0.03846 0.02951 -0.0504 1.0000 0.0489
-10.500 -0.9526 0.03699 0.02804 -0.0494 1.0000 0.0501
-10.250 -0.9428 0.03556 0.02656 -0.0485 1.0000 0.0516
-10.000 -0.9318 0.03418 0.02510 -0.0477 1.0000 0.0536
-9.750 -0.9193 0.03288 0.02368 -0.0468 1.0000 0.0561
-9.500 -0.9077 0.03153 0.02237 -0.0461 1.0000 0.0585
-9.250 -0.8937 0.03032 0.02112 -0.0453 1.0000 0.0617
-9.000 -0.8786 0.02915 0.01987 -0.0445 1.0000 0.0653
-8.750 -0.8630 0.02794 0.01869 -0.0441 1.0000 0.0694
-8.500 -0.8454 0.02686 0.01757 -0.0437 1.0000 0.0755
-8.250 -0.8268 0.02577 0.01649 -0.0436 1.0000 0.0830
-8.000 -0.8069 0.02472 0.01546 -0.0436 1.0000 0.0929
-7.750 -0.7858 0.02371 0.01449 -0.0438 1.0000 0.1053
-7.500 -0.7635 0.02277 0.01358 -0.0440 1.0000 0.1207
-7.250 -0.7401 0.02191 0.01272 -0.0444 1.0000 0.1381
-7.000 -0.7159 0.02104 0.01190 -0.0449 1.0000 0.1573
-6.750 -0.6908 0.02015 0.01111 -0.0457 1.0000 0.1803
-6.500 -0.6646 0.01923 0.01032 -0.0467 1.0000 0.2103
-6.250 -0.6373 0.01826 0.00960 -0.0480 1.0000 0.2543
-6.000 -0.6097 0.01747 0.00917 -0.0492 1.0000 0.3165
-5.750 -0.5832 0.01716 0.00910 -0.0494 1.0000 0.3723
-5.500 -0.5569 0.01708 0.00907 -0.0493 1.0000 0.4097
-5.250 -0.5312 0.01712 0.00911 -0.0489 1.0000 0.4346
-5.000 -0.5050 0.01714 0.00906 -0.0487 1.0000 0.4545
-4.750 -0.4792 0.01721 0.00905 -0.0483 1.0000 0.4702
-4.500 -0.4538 0.01729 0.00910 -0.0478 1.0000 0.4828
-4.250 -0.4280 0.01736 0.00910 -0.0474 1.0000 0.4947
-4.000 -0.4012 0.01738 0.00902 -0.0474 1.0000 0.5071
-3.750 -0.3770 0.01755 0.00920 -0.0465 1.0000 0.5163
-3.500 -0.3510 0.01763 0.00923 -0.0462 1.0000 0.5264
-3.250 -0.3255 0.01777 0.00934 -0.0457 1.0000 0.5374
-3.000 -0.3021 0.01804 0.00965 -0.0446 1.0000 0.5472
-2.750 -0.2758 0.01815 0.00973 -0.0444 1.0000 0.5585
-2.500 -0.2519 0.01829 0.00992 -0.0434 1.0000 0.5644
-2.250 -0.2245 0.01826 0.00985 -0.0437 1.0000 0.5711
-2.000 -0.1974 0.01823 0.00980 -0.0438 1.0000 0.5765
-1.750 -0.1723 0.01829 0.00990 -0.0433 1.0000 0.5807
-1.500 -0.1455 0.01829 0.00991 -0.0434 1.0000 0.5860
-1.250 -0.1169 0.01825 0.00984 -0.0440 1.0000 0.5923
-1.000 -0.0920 0.01833 0.01000 -0.0435 1.0000 0.5959
-0.750 -0.0663 0.01840 0.01013 -0.0433 1.0000 0.6003
-0.500 -0.0391 0.01845 0.01021 -0.0436 1.0000 0.6058
-0.250 -0.0118 0.01850 0.01031 -0.0439 1.0000 0.6107
0.250 0.0426 0.01875 0.01076 -0.0441 0.9985 0.6190
0.500 0.0781 0.01886 0.01096 -0.0460 0.9956 0.6246
0.750 0.1842 0.01810 0.01045 -0.0603 0.9520 0.6298
1.000 0.2584 0.01665 0.00921 -0.0666 0.8959 0.6345
1.250 0.3047 0.01797 0.00784 -0.0670 0.2373 0.6390
1.500 0.3300 0.01900 0.00817 -0.0669 0.1150 0.6442
1.750 0.3549 0.01952 0.00861 -0.0661 0.0924 0.6476
2.000 0.3803 0.02003 0.00910 -0.0655 0.0825 0.6517
2.250 0.4068 0.02048 0.00956 -0.0651 0.0751 0.6565
2.500 0.4335 0.02105 0.01009 -0.0650 0.0698 0.6617
2.750 0.4582 0.02162 0.01076 -0.0642 0.0663 0.6652
3.000 0.4835 0.02228 0.01140 -0.0636 0.0630 0.6696
3.250 0.5099 0.02307 0.01215 -0.0633 0.0599 0.6747
3.500 0.5378 0.02381 0.01297 -0.0632 0.0571 0.6796
3.750 0.5642 0.02467 0.01390 -0.0627 0.0552 0.6836
4.000 0.5912 0.02560 0.01483 -0.0625 0.0532 0.6885
4.250 0.6195 0.02669 0.01599 -0.0625 0.0511 0.6942
4.500 0.6469 0.02776 0.01729 -0.0622 0.0490 0.6987
4.750 0.6738 0.02904 0.01876 -0.0617 0.0476 0.7033
5.000 0.7008 0.03035 0.02022 -0.0615 0.0464 0.7090
5.250 0.7268 0.03163 0.02156 -0.0613 0.0449 0.7145
5.500 0.7509 0.03334 0.02369 -0.0604 0.0433 0.7193
5.750 0.7748 0.03541 0.02621 -0.0595 0.0421 0.7249
6.000 0.7973 0.03778 0.02900 -0.0585 0.0414 0.7304
6.250 0.8168 0.04033 0.03199 -0.0571 0.0408 0.7354
6.500 0.8355 0.04286 0.03489 -0.0559 0.0400 0.7414
6.750 0.8544 0.04483 0.03707 -0.0549 0.0390 0.7473
7.000 0.8740 0.04628 0.03854 -0.0543 0.0382 0.7532
7.250 0.8820 0.05060 0.04353 -0.0520 0.0374 0.7590
7.500 0.8886 0.05490 0.04832 -0.0498 0.0373 0.7644
7.750 0.8924 0.05928 0.05313 -0.0478 0.0373 0.7701
8.000 0.8941 0.06380 0.05800 -0.0461 0.0373 0.7765
8.250 0.8929 0.06818 0.06267 -0.0445 0.0375 0.7821
8.500 0.8897 0.07252 0.06725 -0.0431 0.0377 0.7885
8.750 0.8854 0.07666 0.07157 -0.0420 0.0378 0.7954
9.000 0.8792 0.08059 0.07565 -0.0409 0.0380 0.8024
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