NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 500,000 Max Cl/Cd: 49.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9510-il-500000-n5.txt Download as CSV file: xf-npl9510-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0373 0.15102 0.14781 0.0038 1.0000 0.0158
-19.500 -1.0530 0.14321 0.13988 -0.0007 1.0000 0.0159
-19.250 -1.0676 0.13586 0.13243 -0.0048 1.0000 0.0160
-19.000 -1.0814 0.12887 0.12533 -0.0086 1.0000 0.0161
-18.750 -1.0948 0.12212 0.11847 -0.0123 1.0000 0.0162
-18.500 -1.1072 0.11566 0.11190 -0.0157 1.0000 0.0163
-18.250 -1.1188 0.10953 0.10566 -0.0189 1.0000 0.0164
-18.000 -1.1294 0.10368 0.09970 -0.0219 1.0000 0.0165
-17.750 -1.1392 0.09807 0.09397 -0.0247 1.0000 0.0166
-17.500 -1.1481 0.09273 0.08852 -0.0274 1.0000 0.0168
-17.250 -1.1561 0.08766 0.08334 -0.0299 1.0000 0.0169
-17.000 -1.1629 0.08286 0.07842 -0.0322 1.0000 0.0170
-16.750 -1.1688 0.07833 0.07379 -0.0343 1.0000 0.0171
-16.500 -1.1735 0.07406 0.06940 -0.0362 1.0000 0.0173
-16.250 -1.1771 0.07003 0.06526 -0.0380 1.0000 0.0174
-16.000 -1.1798 0.06624 0.06137 -0.0396 1.0000 0.0175
-15.750 -1.1814 0.06268 0.05770 -0.0411 1.0000 0.0177
-15.500 -1.1821 0.05932 0.05423 -0.0424 1.0000 0.0178
-15.250 -1.1820 0.05616 0.05097 -0.0436 1.0000 0.0179
-15.000 -1.1809 0.05319 0.04790 -0.0446 1.0000 0.0180
-14.750 -1.1821 0.05015 0.04478 -0.0456 1.0000 0.0182
-14.500 -1.1826 0.04724 0.04181 -0.0464 1.0000 0.0185
-14.250 -1.1812 0.04460 0.03910 -0.0472 1.0000 0.0187
-14.000 -1.1781 0.04217 0.03661 -0.0478 1.0000 0.0189
-13.750 -1.1736 0.03993 0.03430 -0.0483 1.0000 0.0192
-13.500 -1.1682 0.03780 0.03211 -0.0488 1.0000 0.0194
-13.250 -1.1623 0.03578 0.03002 -0.0491 1.0000 0.0196
-13.000 -1.1560 0.03386 0.02803 -0.0493 1.0000 0.0199
-12.750 -1.1493 0.03204 0.02615 -0.0494 1.0000 0.0202
-12.500 -1.1432 0.03034 0.02438 -0.0492 1.0000 0.0205
-12.250 -1.1395 0.02875 0.02273 -0.0483 1.0000 0.0207
-12.000 -1.1375 0.02727 0.02119 -0.0470 1.0000 0.0210
-11.750 -1.1295 0.02584 0.01969 -0.0467 1.0000 0.0213
-11.500 -1.1178 0.02453 0.01830 -0.0467 1.0000 0.0215
-11.250 -1.1045 0.02306 0.01678 -0.0473 1.0000 0.0220
-11.000 -1.0878 0.02190 0.01557 -0.0477 1.0000 0.0225
-10.750 -1.0696 0.02101 0.01463 -0.0476 1.0000 0.0230
-10.500 -1.0499 0.02023 0.01380 -0.0476 1.0000 0.0237
-10.250 -1.0291 0.01954 0.01305 -0.0475 1.0000 0.0244
-10.000 -0.9999 0.01885 0.01230 -0.0490 0.9991 0.0253
-9.750 -0.9696 0.01805 0.01146 -0.0508 0.9979 0.0264
-9.500 -0.9389 0.01736 0.01074 -0.0525 0.9968 0.0277
-9.250 -0.9079 0.01677 0.01011 -0.0541 0.9957 0.0290
-9.000 -0.8764 0.01621 0.00950 -0.0558 0.9948 0.0305
-8.750 -0.8446 0.01563 0.00891 -0.0575 0.9940 0.0327
-8.500 -0.8143 0.01515 0.00841 -0.0587 0.9926 0.0350
-8.250 -0.7838 0.01463 0.00789 -0.0600 0.9913 0.0382
-8.000 -0.7528 0.01417 0.00742 -0.0613 0.9900 0.0422
-7.750 -0.7214 0.01371 0.00697 -0.0627 0.9888 0.0477
-7.500 -0.6897 0.01324 0.00653 -0.0641 0.9878 0.0553
-7.250 -0.6576 0.01279 0.00613 -0.0656 0.9868 0.0660
-7.000 -0.6252 0.01232 0.00575 -0.0672 0.9860 0.0805
-6.750 -0.5925 0.01193 0.00541 -0.0688 0.9852 0.0953
-6.500 -0.5595 0.01158 0.00511 -0.0703 0.9845 0.1085
-6.250 -0.5261 0.01123 0.00482 -0.0719 0.9839 0.1229
-6.000 -0.4957 0.01090 0.00455 -0.0729 0.9821 0.1395
-5.750 -0.4646 0.01054 0.00427 -0.0740 0.9804 0.1587
-5.500 -0.4329 0.01018 0.00400 -0.0752 0.9790 0.1801
-5.250 -0.4004 0.00978 0.00373 -0.0766 0.9779 0.2088
-5.000 -0.3669 0.00914 0.00338 -0.0786 0.9770 0.2719
-4.750 -0.3332 0.00857 0.00310 -0.0805 0.9762 0.3434
-4.500 -0.2998 0.00832 0.00297 -0.0819 0.9752 0.3786
-4.250 -0.2667 0.00816 0.00289 -0.0832 0.9743 0.4033
-4.000 -0.2338 0.00806 0.00282 -0.0843 0.9733 0.4193
-3.750 -0.2009 0.00798 0.00276 -0.0854 0.9725 0.4306
-3.500 -0.1679 0.00792 0.00271 -0.0865 0.9716 0.4417
-3.250 -0.1393 0.00787 0.00270 -0.0866 0.9687 0.4514
-3.000 -0.1092 0.00783 0.00267 -0.0870 0.9664 0.4588
-2.750 -0.0783 0.00779 0.00267 -0.0876 0.9645 0.4671
-2.500 -0.0469 0.00776 0.00267 -0.0883 0.9628 0.4785
-2.250 -0.0153 0.00775 0.00268 -0.0890 0.9614 0.4898
-2.000 0.0165 0.00771 0.00272 -0.0898 0.9600 0.4979
-1.750 0.0494 0.00768 0.00269 -0.0907 0.9583 0.5053
-1.500 0.0774 0.00759 0.00265 -0.0904 0.9507 0.5097
-1.250 0.1069 0.00738 0.00245 -0.0901 0.9347 0.5137
-1.000 0.1343 0.00721 0.00223 -0.0892 0.9072 0.5178
-0.750 0.1620 0.00717 0.00211 -0.0886 0.8797 0.5217
-0.500 0.1893 0.00719 0.00205 -0.0880 0.8417 0.5251
-0.250 0.1979 0.00917 0.00226 -0.0839 0.4070 0.5282
0.000 0.2199 0.01030 0.00252 -0.0832 0.1700 0.5317
0.250 0.2467 0.01073 0.00265 -0.0830 0.0954 0.5355
0.500 0.2744 0.01099 0.00277 -0.0830 0.0652 0.5392
0.750 0.3025 0.01117 0.00291 -0.0829 0.0540 0.5424
1.000 0.3307 0.01134 0.00306 -0.0829 0.0481 0.5459
1.250 0.3588 0.01153 0.00323 -0.0828 0.0438 0.5495
1.500 0.3869 0.01170 0.00340 -0.0827 0.0410 0.5530
1.750 0.4148 0.01193 0.00360 -0.0826 0.0387 0.5565
2.000 0.4426 0.01214 0.00383 -0.0825 0.0371 0.5598
2.250 0.4705 0.01234 0.00405 -0.0823 0.0355 0.5631
2.500 0.4982 0.01256 0.00427 -0.0822 0.0339 0.5665
2.750 0.5254 0.01287 0.00457 -0.0820 0.0326 0.5699
3.000 0.5529 0.01314 0.00485 -0.0817 0.0317 0.5735
3.250 0.5803 0.01339 0.00514 -0.0815 0.0306 0.5769
3.500 0.6077 0.01365 0.00542 -0.0813 0.0295 0.5803
3.750 0.6348 0.01393 0.00571 -0.0811 0.0285 0.5837
4.000 0.6612 0.01436 0.00613 -0.0807 0.0276 0.5873
4.250 0.6882 0.01470 0.00651 -0.0804 0.0270 0.5909
4.500 0.7149 0.01506 0.00693 -0.0800 0.0263 0.5944
4.750 0.7416 0.01541 0.00733 -0.0797 0.0254 0.5981
5.000 0.7683 0.01575 0.00769 -0.0794 0.0247 0.6019
5.250 0.7948 0.01611 0.00806 -0.0790 0.0240 0.6056
5.500 0.8206 0.01665 0.00862 -0.0786 0.0234 0.6093
5.750 0.8469 0.01710 0.00917 -0.0782 0.0228 0.6131
6.000 0.8729 0.01760 0.00976 -0.0777 0.0222 0.6172
6.250 0.8987 0.01811 0.01035 -0.0772 0.0217 0.6214
6.500 0.9246 0.01861 0.01090 -0.0768 0.0212 0.6254
6.750 0.9502 0.01909 0.01145 -0.0763 0.0207 0.6293
7.000 0.9757 0.01959 0.01200 -0.0758 0.0204 0.6338
7.250 1.0005 0.02020 0.01266 -0.0753 0.0200 0.6385
7.500 1.0251 0.02094 0.01351 -0.0746 0.0196 0.6430
7.750 1.0496 0.02168 0.01442 -0.0740 0.0191 0.6471
8.000 1.0737 0.02245 0.01536 -0.0732 0.0186 0.6520
8.250 1.0974 0.02327 0.01631 -0.0725 0.0182 0.6573
8.500 1.1207 0.02407 0.01724 -0.0717 0.0179 0.6624
8.750 1.1437 0.02483 0.01814 -0.0709 0.0176 0.6675
9.000 1.1664 0.02556 0.01898 -0.0701 0.0173 0.6730
9.250 1.1888 0.02630 0.01979 -0.0692 0.0171 0.6786
9.500 1.2103 0.02709 0.02071 -0.0682 0.0169 0.6845
9.750 1.2305 0.02809 0.02183 -0.0671 0.0167 0.6910
10.000 1.2481 0.02959 0.02354 -0.0656 0.0165 0.6970
10.250 1.2632 0.03149 0.02576 -0.0639 0.0163 0.7028
10.500 1.2741 0.03398 0.02863 -0.0617 0.0160 0.7089
10.750 1.2776 0.03741 0.03253 -0.0587 0.0157 0.7144
11.000 1.2552 0.04436 0.04023 -0.0535 0.0153 0.7187
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