NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S818 Airfoil (s818-nr) Reynolds number: 1,000,000 Max Cl/Cd: 105.85 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s818-nr-1000000.txt Download as CSV file: xf-s818-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S818 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7526 0.08924 0.08521 -0.0372 1.0000 0.0546
-14.250 -0.7493 0.08733 0.08335 -0.0370 1.0000 0.0605
-14.000 -0.7445 0.08532 0.08137 -0.0371 0.9999 0.0659
-13.750 -0.7194 0.08180 0.07787 -0.0432 0.9973 0.0743
-13.500 -0.7022 0.07837 0.07452 -0.0480 0.9951 0.0872
-13.250 -0.6929 0.07418 0.07045 -0.0530 0.9935 0.1067
-13.000 -0.7046 0.06843 0.06483 -0.0569 0.9914 0.1316
-12.750 -0.7419 0.06049 0.05703 -0.0605 0.9876 0.1615
-12.500 -0.7785 0.05268 0.04925 -0.0647 0.9849 0.1824
-12.250 -0.8184 0.04441 0.04094 -0.0699 0.9825 0.1966
-12.000 -0.8572 0.03794 0.03440 -0.0721 0.9779 0.2041
-11.750 -0.8933 0.03191 0.02827 -0.0742 0.9715 0.2099
-11.500 -0.9215 0.02624 0.02248 -0.0773 0.9655 0.2159
-11.250 -0.9583 0.01869 0.01483 -0.0825 0.9551 0.2313
-11.000 -0.9433 0.01336 0.00960 -0.0926 0.9470 0.2947
-10.750 -0.9047 0.01298 0.00923 -0.0956 0.9450 0.3048
-10.500 -0.8653 0.01278 0.00895 -0.0983 0.9435 0.3096
-10.250 -0.8265 0.01257 0.00875 -0.1010 0.9425 0.3139
-10.000 -0.7874 0.01252 0.00867 -0.1035 0.9416 0.3172
-9.750 -0.7482 0.01244 0.00856 -0.1060 0.9409 0.3197
-9.500 -0.7082 0.01232 0.00838 -0.1087 0.9403 0.3213
-9.250 -0.6961 0.01219 0.00820 -0.1059 0.9315 0.3221
-9.000 -0.6607 0.01190 0.00789 -0.1078 0.9291 0.3250
-8.750 -0.6236 0.01176 0.00776 -0.1098 0.9272 0.3273
-8.500 -0.6029 0.01169 0.00768 -0.1085 0.9193 0.3286
-8.250 -0.5746 0.01152 0.00751 -0.1088 0.9133 0.3297
-8.000 -0.5490 0.01137 0.00733 -0.1085 0.9043 0.3305
-7.500 -0.4710 0.01099 0.00688 -0.1131 0.8878 0.3328
-7.250 -0.4130 0.01076 0.00657 -0.1194 0.8776 0.3338
-7.000 -0.3440 0.01053 0.00619 -0.1281 0.8576 0.3341
-6.750 -0.3045 0.01047 0.00592 -0.1308 0.8205 0.3343
-6.500 -0.2803 0.01049 0.00573 -0.1303 0.7829 0.3346
-6.250 -0.2581 0.01049 0.00557 -0.1294 0.7512 0.3348
-6.000 -0.2353 0.01048 0.00541 -0.1287 0.7243 0.3351
-5.750 -0.2114 0.01046 0.00526 -0.1282 0.7005 0.3353
-5.500 -0.1870 0.01044 0.00512 -0.1278 0.6791 0.3356
-5.250 -0.1617 0.01042 0.00498 -0.1275 0.6596 0.3358
-5.000 -0.1357 0.01039 0.00486 -0.1274 0.6416 0.3361
-4.750 -0.1093 0.01037 0.00474 -0.1274 0.6247 0.3363
-4.250 -0.0550 0.01034 0.00453 -0.1276 0.5941 0.3367
-4.000 -0.0273 0.01032 0.00444 -0.1278 0.5805 0.3369
-3.750 0.0004 0.01032 0.00437 -0.1279 0.5679 0.3372
-3.500 0.0280 0.01034 0.00430 -0.1281 0.5555 0.3374
-3.250 0.0565 0.01021 0.00412 -0.1285 0.5440 0.3382
-3.000 0.0849 0.01011 0.00397 -0.1289 0.5333 0.3393
-2.500 0.1419 0.01003 0.00380 -0.1296 0.5129 0.3409
-2.250 0.1702 0.01003 0.00375 -0.1299 0.5038 0.3416
-2.000 0.1992 0.01002 0.00371 -0.1303 0.4958 0.3422
-1.750 0.2273 0.01005 0.00369 -0.1305 0.4876 0.3429
-1.500 0.2564 0.01004 0.00367 -0.1309 0.4811 0.3436
-1.250 0.2847 0.01007 0.00366 -0.1312 0.4742 0.3442
-1.000 0.3133 0.01009 0.00366 -0.1315 0.4682 0.3449
-0.750 0.3421 0.01010 0.00365 -0.1318 0.4626 0.3456
-0.500 0.3702 0.01014 0.00366 -0.1320 0.4570 0.3463
-0.250 0.3986 0.01018 0.00367 -0.1322 0.4521 0.3471
0.000 0.4274 0.01018 0.00368 -0.1325 0.4480 0.3478
0.250 0.4559 0.01022 0.00370 -0.1328 0.4437 0.3486
0.500 0.4838 0.01028 0.00373 -0.1329 0.4393 0.3493
0.750 0.5119 0.01033 0.00376 -0.1331 0.4356 0.3500
1.000 0.5408 0.01034 0.00379 -0.1334 0.4326 0.3507
1.250 0.5691 0.01038 0.00382 -0.1336 0.4293 0.3513
1.500 0.5971 0.01044 0.00387 -0.1337 0.4261 0.3518
1.750 0.6247 0.01053 0.00393 -0.1337 0.4230 0.3523
2.000 0.6523 0.01061 0.00399 -0.1338 0.4196 0.3530
2.250 0.6821 0.01057 0.00399 -0.1343 0.4179 0.3548
2.500 0.7111 0.01057 0.00403 -0.1347 0.4160 0.3564
2.750 0.7398 0.01061 0.00409 -0.1350 0.4140 0.3577
3.000 0.7681 0.01067 0.00417 -0.1352 0.4118 0.3589
3.250 0.7961 0.01074 0.00426 -0.1353 0.4098 0.3601
3.500 0.8237 0.01084 0.00437 -0.1353 0.4076 0.3612
3.750 0.8511 0.01096 0.00449 -0.1353 0.4052 0.3624
4.000 0.8789 0.01111 0.00464 -0.1354 0.4028 0.3635
4.250 0.9071 0.01117 0.00474 -0.1356 0.4017 0.3647
4.500 0.9352 0.01124 0.00485 -0.1357 0.4003 0.3658
4.750 0.9631 0.01133 0.00496 -0.1358 0.3988 0.3667
5.000 0.9909 0.01142 0.00509 -0.1358 0.3973 0.3675
5.250 1.0184 0.01153 0.00522 -0.1358 0.3959 0.3681
5.500 1.0471 0.01159 0.00532 -0.1361 0.3944 0.3706
5.750 1.0750 0.01169 0.00546 -0.1363 0.3929 0.3727
6.000 1.1020 0.01182 0.00562 -0.1362 0.3907 0.3745
6.250 1.1282 0.01204 0.00583 -0.1360 0.3858 0.3761
6.500 1.1534 0.01200 0.00587 -0.1355 0.3807 0.3778
6.750 1.1787 0.01209 0.00596 -0.1351 0.3753 0.3795
7.000 1.2035 0.01228 0.00615 -0.1347 0.3713 0.3810
7.250 1.2294 0.01243 0.00633 -0.1344 0.3684 0.3824
7.500 1.2561 0.01249 0.00645 -0.1342 0.3653 0.3835
7.750 1.2823 0.01259 0.00659 -0.1340 0.3614 0.3850
8.000 1.3077 0.01272 0.00675 -0.1337 0.3576 0.3878
8.250 1.3310 0.01295 0.00700 -0.1330 0.3528 0.3901
8.500 1.3580 0.01300 0.00714 -0.1329 0.3490 0.3922
8.750 1.3830 0.01314 0.00732 -0.1325 0.3434 0.3942
9.000 1.4052 0.01340 0.00756 -0.1317 0.3369 0.3962
9.250 1.4311 0.01352 0.00775 -0.1314 0.3307 0.3980
9.500 1.4526 0.01380 0.00801 -0.1304 0.3210 0.3995
9.750 1.4742 0.01409 0.00828 -0.1295 0.3067 0.4013
10.000 1.4902 0.01465 0.00874 -0.1277 0.2791 0.4044
10.250 1.4930 0.01590 0.00972 -0.1241 0.2341 0.4064
10.500 1.4951 0.01717 0.01080 -0.1204 0.2007 0.4084
10.750 1.4973 0.01846 0.01193 -0.1169 0.1710 0.4104
11.000 1.4997 0.01974 0.01309 -0.1136 0.1471 0.4123
11.250 1.5021 0.02105 0.01430 -0.1104 0.1276 0.4142
11.500 1.5049 0.02238 0.01556 -0.1074 0.1123 0.4158
11.750 1.5085 0.02373 0.01688 -0.1048 0.0997 0.4178
12.000 1.5134 0.02510 0.01824 -0.1025 0.0900 0.4211
12.250 1.5168 0.02662 0.01977 -0.1003 0.0816 0.4237
12.500 1.5198 0.02827 0.02142 -0.0982 0.0746 0.4263
12.750 1.5239 0.02994 0.02313 -0.0965 0.0689 0.4288
13.000 1.5245 0.03197 0.02517 -0.0947 0.0633 0.4310
13.250 1.5276 0.03395 0.02719 -0.0933 0.0589 0.4329
13.500 1.5276 0.03635 0.02962 -0.0921 0.0544 0.4360
13.750 1.5284 0.03880 0.03213 -0.0912 0.0506 0.4393
14.000 1.5284 0.04147 0.03485 -0.0904 0.0472 0.4423
14.250 1.5250 0.04460 0.03802 -0.0898 0.0439 0.4452
14.500 1.5257 0.04743 0.04092 -0.0895 0.0417 0.4480
14.750 1.5228 0.05074 0.04428 -0.0893 0.0393 0.4503
15.000 1.5179 0.05443 0.04804 -0.0893 0.0368 0.4541
15.250 1.5172 0.05773 0.05144 -0.0895 0.0353 0.4581
15.500 1.5146 0.06133 0.05511 -0.0898 0.0337 0.4618
15.750 1.5095 0.06527 0.05912 -0.0902 0.0321 0.4650
16.000 1.5035 0.06943 0.06334 -0.0907 0.0304 0.4679
16.250 1.5033 0.07297 0.06698 -0.0913 0.0294 0.4727
16.500 1.5017 0.07671 0.07079 -0.0920 0.0282 0.4770
16.750 1.4984 0.08070 0.07485 -0.0928 0.0270 0.4809
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