NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S814 Airfoil (s814-nr) Reynolds number: 500,000 Max Cl/Cd: 84.38 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s814-nr-500000.txt Download as CSV file: xf-s814-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S814 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2491 0.10064 0.09705 -0.0483 0.9868 0.2588
-9.500 -0.2199 0.09931 0.09571 -0.0510 0.9848 0.2598
-9.250 -0.2540 0.09133 0.08763 -0.0577 0.9825 0.2684
-9.000 -0.2101 0.09099 0.08730 -0.0599 0.9815 0.2677
-8.750 -0.1603 0.09119 0.08751 -0.0618 0.9807 0.2660
-8.500 -0.1347 0.09066 0.08700 -0.0630 0.9771 0.2720
-8.250 -0.6151 0.02894 0.02457 -0.0898 0.9397 0.3014
-8.000 -0.6095 0.02557 0.02108 -0.0942 0.9279 0.3028
-7.750 -0.5777 0.02383 0.01924 -0.0986 0.9243 0.3037
-7.500 -0.5625 0.02243 0.01776 -0.0990 0.9136 0.3044
-7.250 -0.5309 0.02128 0.01653 -0.1017 0.9092 0.3051
-7.000 -0.5112 0.02031 0.01548 -0.1017 0.8979 0.3057
-6.750 -0.4751 0.01939 0.01449 -0.1046 0.8928 0.3065
-6.500 -0.4444 0.01862 0.01364 -0.1063 0.8820 0.3072
-6.250 -0.3982 0.01780 0.01273 -0.1108 0.8755 0.3079
-6.000 -0.3498 0.01712 0.01196 -0.1158 0.8640 0.3087
-5.750 -0.2924 0.01654 0.01125 -0.1225 0.8499 0.3096
-5.500 -0.2449 0.01607 0.01062 -0.1271 0.8284 0.3103
-5.250 -0.2106 0.01574 0.01011 -0.1291 0.8031 0.3110
-5.000 -0.1819 0.01549 0.00969 -0.1298 0.7784 0.3116
-4.750 -0.1556 0.01530 0.00934 -0.1300 0.7558 0.3121
-4.500 -0.1302 0.01513 0.00902 -0.1300 0.7345 0.3126
-4.250 -0.1048 0.01499 0.00875 -0.1300 0.7149 0.3130
-4.000 -0.0791 0.01487 0.00850 -0.1299 0.6969 0.3134
-3.750 -0.0542 0.01435 0.00786 -0.1301 0.6803 0.3145
-3.500 -0.0286 0.01410 0.00753 -0.1301 0.6650 0.3154
-3.250 -0.0026 0.01397 0.00733 -0.1300 0.6506 0.3162
-3.000 0.0237 0.01388 0.00718 -0.1299 0.6368 0.3169
-2.750 0.0505 0.01380 0.00705 -0.1299 0.6240 0.3176
-2.500 0.0776 0.01375 0.00696 -0.1299 0.6124 0.3184
-2.000 0.1326 0.01369 0.00682 -0.1302 0.5917 0.3202
-1.750 0.1603 0.01369 0.00675 -0.1303 0.5828 0.3212
-1.500 0.1887 0.01362 0.00666 -0.1306 0.5743 0.3222
-1.250 0.2169 0.01360 0.00656 -0.1308 0.5666 0.3231
-1.000 0.2459 0.01352 0.00647 -0.1312 0.5594 0.3241
-0.750 0.2746 0.01349 0.00638 -0.1316 0.5526 0.3251
-0.500 0.3038 0.01347 0.00630 -0.1320 0.5467 0.3260
-0.250 0.3331 0.01341 0.00623 -0.1324 0.5406 0.3269
0.000 0.3621 0.01341 0.00618 -0.1328 0.5349 0.3277
0.250 0.3917 0.01344 0.00616 -0.1332 0.5298 0.3283
0.500 0.4213 0.01328 0.00600 -0.1337 0.5251 0.3295
0.750 0.4505 0.01317 0.00591 -0.1342 0.5206 0.3310
1.000 0.4799 0.01318 0.00591 -0.1346 0.5165 0.3322
1.250 0.5098 0.01322 0.00596 -0.1350 0.5127 0.3334
1.500 0.5391 0.01322 0.00601 -0.1353 0.5091 0.3346
1.750 0.5685 0.01324 0.00606 -0.1357 0.5056 0.3358
2.000 0.5980 0.01329 0.00611 -0.1360 0.5022 0.3372
2.250 0.6282 0.01338 0.00617 -0.1365 0.4987 0.3386
2.500 0.6587 0.01346 0.00625 -0.1371 0.4955 0.3400
2.750 0.6881 0.01348 0.00631 -0.1374 0.4928 0.3414
3.000 0.7178 0.01353 0.00638 -0.1377 0.4900 0.3428
3.250 0.7476 0.01361 0.00645 -0.1381 0.4872 0.3438
3.500 0.7776 0.01358 0.00645 -0.1386 0.4845 0.3459
3.750 0.8081 0.01366 0.00656 -0.1392 0.4815 0.3479
4.000 0.8383 0.01379 0.00673 -0.1396 0.4783 0.3497
4.250 0.8657 0.01382 0.00684 -0.1395 0.4751 0.3515
4.500 0.8937 0.01388 0.00695 -0.1394 0.4715 0.3533
4.750 0.9217 0.01394 0.00704 -0.1394 0.4679 0.3552
5.000 0.9511 0.01409 0.00715 -0.1397 0.4637 0.3572
5.250 0.9781 0.01417 0.00727 -0.1395 0.4596 0.3589
5.500 1.0036 0.01420 0.00734 -0.1389 0.4549 0.3603
5.750 1.0299 0.01414 0.00735 -0.1386 0.4501 0.3631
6.000 1.0578 0.01430 0.00751 -0.1386 0.4447 0.3652
6.250 1.0811 0.01430 0.00762 -0.1376 0.4399 0.3673
6.500 1.1057 0.01435 0.00773 -0.1369 0.4351 0.3696
6.750 1.1309 0.01448 0.00786 -0.1363 0.4301 0.3719
7.000 1.1540 0.01457 0.00800 -0.1354 0.4249 0.3741
7.250 1.1745 0.01461 0.00809 -0.1338 0.4188 0.3759
7.500 1.1962 0.01469 0.00817 -0.1326 0.4120 0.3787
7.750 1.2181 0.01473 0.00834 -0.1315 0.4056 0.3814
8.000 1.2395 0.01487 0.00854 -0.1302 0.3984 0.3840
8.250 1.2608 0.01505 0.00877 -0.1290 0.3909 0.3867
8.500 1.2816 0.01523 0.00898 -0.1276 0.3812 0.3894
8.750 1.3020 0.01543 0.00921 -0.1262 0.3694 0.3918
9.000 1.3206 0.01569 0.00946 -0.1246 0.3540 0.3942
9.250 1.3353 0.01609 0.00982 -0.1225 0.3301 0.3970
9.500 1.3433 0.01684 0.01043 -0.1194 0.2958 0.3993
9.750 1.3470 0.01792 0.01132 -0.1159 0.2615 0.4014
10.000 1.3498 0.01910 0.01234 -0.1124 0.2315 0.4036
10.250 1.3536 0.02029 0.01340 -0.1092 0.2048 0.4058
10.500 1.3567 0.02156 0.01455 -0.1060 0.1820 0.4079
10.750 1.3602 0.02286 0.01576 -0.1031 0.1622 0.4096
11.000 1.3637 0.02421 0.01707 -0.1005 0.1451 0.4124
11.250 1.3664 0.02569 0.01853 -0.0980 0.1302 0.4148
11.500 1.3689 0.02729 0.02011 -0.0957 0.1175 0.4171
11.750 1.3708 0.02902 0.02183 -0.0936 0.1064 0.4196
12.000 1.3711 0.03099 0.02378 -0.0916 0.0966 0.4220
12.250 1.3729 0.03299 0.02578 -0.0900 0.0881 0.4245
12.500 1.3744 0.03512 0.02792 -0.0886 0.0811 0.4266
12.750 1.3743 0.03757 0.03041 -0.0875 0.0745 0.4296
13.000 1.3768 0.03991 0.03281 -0.0866 0.0690 0.4323
13.250 1.3750 0.04274 0.03567 -0.0859 0.0640 0.4348
13.500 1.3766 0.04536 0.03835 -0.0853 0.0597 0.4375
13.750 1.3759 0.04832 0.04135 -0.0850 0.0559 0.4400
14.000 1.3734 0.05156 0.04463 -0.0847 0.0524 0.4423
14.250 1.3757 0.05439 0.04753 -0.0847 0.0494 0.4452
14.500 1.3740 0.05776 0.05097 -0.0848 0.0467 0.4480
14.750 1.3714 0.06131 0.05458 -0.0850 0.0442 0.4508
15.000 1.3740 0.06429 0.05766 -0.0852 0.0422 0.4541
15.250 1.3735 0.06771 0.06112 -0.0856 0.0402 0.4573
15.500 1.3696 0.07163 0.06507 -0.0861 0.0384 0.4602
15.750 1.3702 0.07510 0.06864 -0.0867 0.0368 0.4639
16.000 1.3729 0.07832 0.07196 -0.0873 0.0353 0.4679
16.250 1.3735 0.08183 0.07555 -0.0880 0.0339 0.4720
16.500 1.3714 0.08578 0.07952 -0.0889 0.0326 0.4757
16.750 1.3675 0.09005 0.08386 -0.0899 0.0314 0.4792
17.000 1.3722 0.09318 0.08712 -0.0907 0.0303 0.4841
17.250 1.3745 0.09665 0.09068 -0.0917 0.0293 0.4891
17.500 1.3759 0.10024 0.09432 -0.0927 0.0283 0.4942
17.750 1.3752 0.10426 0.09842 -0.0941 0.0274 0.4992
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