NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 500,000 Max Cl/Cd: 40.29 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9510-il-500000.txt Download as CSV file: xf-npl9510-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0603 0.10571 0.10229 -0.0258 1.0000 0.0228
-17.250 -1.0858 0.09685 0.09323 -0.0310 1.0000 0.0228
-17.000 -1.1032 0.08985 0.08607 -0.0350 1.0000 0.0229
-16.750 -1.1169 0.08378 0.07986 -0.0384 1.0000 0.0229
-16.500 -1.1278 0.07839 0.07433 -0.0413 1.0000 0.0231
-16.250 -1.1356 0.07367 0.06949 -0.0438 1.0000 0.0233
-16.000 -1.1418 0.06938 0.06507 -0.0459 1.0000 0.0234
-15.750 -1.1470 0.06536 0.06093 -0.0478 1.0000 0.0237
-15.500 -1.1518 0.06157 0.05702 -0.0495 1.0000 0.0239
-15.250 -1.1558 0.05808 0.05339 -0.0508 1.0000 0.0241
-15.000 -1.1584 0.05481 0.04999 -0.0520 1.0000 0.0243
-14.750 -1.1597 0.05177 0.04681 -0.0529 1.0000 0.0246
-14.500 -1.1592 0.04898 0.04388 -0.0536 1.0000 0.0248
-14.250 -1.1572 0.04641 0.04118 -0.0542 1.0000 0.0250
-14.000 -1.1537 0.04404 0.03868 -0.0547 1.0000 0.0252
-13.750 -1.1489 0.04185 0.03636 -0.0551 1.0000 0.0254
-13.500 -1.1429 0.03983 0.03422 -0.0554 1.0000 0.0256
-13.250 -1.1361 0.03784 0.03217 -0.0542 1.0000 0.0260
-13.000 -1.1280 0.03614 0.03044 -0.0537 1.0000 0.0265
-12.750 -1.1193 0.03454 0.02882 -0.0535 1.0000 0.0269
-12.500 -1.1104 0.03301 0.02725 -0.0533 1.0000 0.0273
-12.250 -1.1022 0.03155 0.02574 -0.0528 1.0000 0.0278
-12.000 -1.0959 0.03015 0.02429 -0.0517 1.0000 0.0282
-11.750 -1.0940 0.02885 0.02294 -0.0498 1.0000 0.0285
-11.500 -1.0877 0.02755 0.02158 -0.0486 1.0000 0.0289
-11.250 -1.0783 0.02630 0.02026 -0.0479 1.0000 0.0294
-11.000 -1.0661 0.02513 0.01900 -0.0475 1.0000 0.0298
-10.750 -1.0517 0.02401 0.01781 -0.0473 1.0000 0.0302
-10.500 -1.0399 0.02241 0.01618 -0.0469 1.0000 0.0310
-10.250 -1.0229 0.02136 0.01511 -0.0467 1.0000 0.0318
-10.000 -1.0038 0.02049 0.01421 -0.0466 1.0000 0.0327
-9.750 -0.9832 0.01973 0.01339 -0.0464 1.0000 0.0339
-9.500 -0.9615 0.01908 0.01268 -0.0463 1.0000 0.0350
-9.250 -0.9397 0.01802 0.01158 -0.0467 1.0000 0.0365
-9.000 -0.9163 0.01725 0.01081 -0.0470 1.0000 0.0383
-8.750 -0.8922 0.01665 0.01016 -0.0472 1.0000 0.0403
-8.500 -0.8671 0.01589 0.00937 -0.0477 1.0000 0.0429
-8.250 -0.8416 0.01528 0.00876 -0.0481 1.0000 0.0464
-8.000 -0.8154 0.01465 0.00812 -0.0486 1.0000 0.0512
-7.750 -0.7888 0.01408 0.00759 -0.0492 1.0000 0.0583
-7.500 -0.7615 0.01349 0.00707 -0.0499 1.0000 0.0706
-7.250 -0.7335 0.01294 0.00663 -0.0507 1.0000 0.0896
-7.000 -0.7054 0.01253 0.00630 -0.0514 1.0000 0.1082
-6.750 -0.6773 0.01219 0.00602 -0.0520 1.0000 0.1247
-6.500 -0.6487 0.01184 0.00574 -0.0527 1.0000 0.1421
-6.250 -0.6199 0.01150 0.00547 -0.0535 1.0000 0.1612
-6.000 -0.5906 0.01115 0.00521 -0.0543 1.0000 0.1838
-5.750 -0.5569 0.01061 0.00487 -0.0563 0.9996 0.2246
-5.250 -0.4868 0.00945 0.00431 -0.0609 0.9987 0.3627
-5.000 -0.4530 0.00927 0.00425 -0.0624 0.9978 0.4001
-4.750 -0.4195 0.00921 0.00423 -0.0638 0.9968 0.4270
-4.500 -0.3859 0.00920 0.00428 -0.0651 0.9958 0.4500
-4.250 -0.3521 0.00922 0.00431 -0.0664 0.9949 0.4645
-4.000 -0.3181 0.00927 0.00434 -0.0677 0.9941 0.4760
-3.750 -0.2869 0.00929 0.00437 -0.0685 0.9923 0.4854
-3.500 -0.2545 0.00931 0.00437 -0.0695 0.9906 0.4926
-3.250 -0.2217 0.00934 0.00442 -0.0705 0.9890 0.4997
-3.000 -0.1886 0.00940 0.00444 -0.0717 0.9876 0.5069
-2.750 -0.1553 0.00941 0.00451 -0.0728 0.9864 0.5126
-2.500 -0.1215 0.00947 0.00457 -0.0741 0.9854 0.5188
-2.250 -0.0873 0.00953 0.00466 -0.0754 0.9844 0.5268
-2.000 -0.0550 0.00963 0.00480 -0.0763 0.9828 0.5349
-1.750 -0.0261 0.00970 0.00487 -0.0765 0.9800 0.5415
-1.500 0.0060 0.00972 0.00497 -0.0773 0.9778 0.5470
-1.250 0.0523 0.00951 0.00479 -0.0809 0.9738 0.5523
-1.000 0.1255 0.00857 0.00386 -0.0893 0.9620 0.5573
-0.750 0.1655 0.00814 0.00351 -0.0912 0.9527 0.5613
-0.500 0.1988 0.00789 0.00331 -0.0916 0.9432 0.5650
-0.250 0.2255 0.00770 0.00314 -0.0906 0.9259 0.5690
0.000 0.2518 0.00755 0.00294 -0.0895 0.8960 0.5729
0.250 0.2760 0.00756 0.00273 -0.0877 0.8167 0.5763
0.500 0.2780 0.01052 0.00319 -0.0829 0.2125 0.5792
0.750 0.3020 0.01138 0.00348 -0.0823 0.0760 0.5827
1.000 0.3295 0.01171 0.00373 -0.0821 0.0621 0.5865
1.250 0.3576 0.01196 0.00395 -0.0820 0.0566 0.5904
1.500 0.3846 0.01231 0.00428 -0.0817 0.0523 0.5940
1.750 0.4123 0.01254 0.00456 -0.0815 0.0501 0.5973
2.000 0.4398 0.01281 0.00483 -0.0812 0.0476 0.6010
2.250 0.4665 0.01324 0.00523 -0.0809 0.0453 0.6050
2.500 0.4932 0.01373 0.00572 -0.0805 0.0438 0.6087
2.750 0.5204 0.01404 0.00607 -0.0802 0.0423 0.6121
3.000 0.5474 0.01437 0.00643 -0.0799 0.0407 0.6155
3.250 0.5741 0.01481 0.00685 -0.0796 0.0391 0.6194
3.500 0.5997 0.01572 0.00775 -0.0791 0.0378 0.6235
3.750 0.6273 0.01613 0.00821 -0.0788 0.0369 0.6273
4.000 0.6543 0.01662 0.00879 -0.0784 0.0358 0.6309
4.250 0.6814 0.01708 0.00928 -0.0781 0.0345 0.6346
4.500 0.7083 0.01758 0.00978 -0.0779 0.0334 0.6389
4.750 0.7347 0.01895 0.01116 -0.0776 0.0324 0.6431
5.000 0.7617 0.01951 0.01190 -0.0771 0.0317 0.6471
5.250 0.7883 0.02041 0.01297 -0.0766 0.0309 0.6511
5.500 0.8147 0.02146 0.01417 -0.0761 0.0301 0.6553
5.750 0.8407 0.02245 0.01527 -0.0757 0.0294 0.6598
6.000 0.8666 0.02308 0.01594 -0.0753 0.0287 0.6642
6.250 0.8913 0.02420 0.01712 -0.0749 0.0280 0.6687
6.500 0.9135 0.02634 0.01962 -0.0737 0.0273 0.6733
6.750 0.9342 0.02878 0.02248 -0.0722 0.0269 0.6778
7.000 0.9506 0.03229 0.02649 -0.0702 0.0268 0.6817
7.250 0.9630 0.03636 0.03103 -0.0678 0.0270 0.6857
7.500 0.9746 0.04018 0.03511 -0.0659 0.0275 0.6904
8.500 0.9081 0.07664 0.07374 -0.0529 0.0304 0.7007
8.750 0.8928 0.08173 0.07897 -0.0522 0.0300 0.7043
9.000 0.8706 0.08719 0.08452 -0.0525 0.0298 0.7082
9.250 0.8473 0.09478 0.09217 -0.0574 0.0297 0.7114
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