NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 50,000 Max Cl/Cd: 16.53 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s810-nr-50000-n5.txt Download as CSV file: xf-s810-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S810 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4647 0.15924 0.15250 -0.0423 1.0000 0.1218
-14.500 -0.4400 0.15465 0.14790 -0.0409 1.0000 0.1272
-14.250 -0.4607 0.15217 0.14556 -0.0453 1.0000 0.1357
-14.000 -0.4320 0.14790 0.14125 -0.0433 1.0000 0.1431
-13.750 -0.4325 0.14451 0.13794 -0.0448 1.0000 0.1534
-13.500 -0.4340 0.14135 0.13486 -0.0461 1.0000 0.1659
-13.250 -0.4283 0.13829 0.13182 -0.0463 1.0000 0.1803
-13.000 -0.4172 0.13566 0.12922 -0.0457 1.0000 0.1978
-12.750 -0.4119 0.13347 0.12710 -0.0450 1.0000 0.2239
-12.500 -0.3557 0.10690 0.10108 -0.0715 0.9777 0.0651
-12.250 -0.3492 0.10217 0.09634 -0.0734 0.9729 0.0616
-12.000 -0.3637 0.09602 0.09013 -0.0771 0.9693 0.0588
-11.750 -0.4173 0.08927 0.08309 -0.0813 0.9643 0.0522
-11.250 -0.5343 0.09020 0.08387 -0.0731 0.9823 0.0609
-11.000 -0.5479 0.08545 0.07893 -0.0760 0.9722 0.0585
-10.750 -0.5717 0.08142 0.07458 -0.0777 0.9612 0.0558
-10.500 -0.5673 0.07756 0.07045 -0.0787 0.9539 0.0494
-10.250 -0.5716 0.07416 0.06685 -0.0791 0.9458 0.0478
-10.000 -0.5797 0.07112 0.06354 -0.0783 0.9377 0.0465
-9.750 -0.5857 0.06853 0.06068 -0.0769 0.9305 0.0457
-9.500 -0.5908 0.06623 0.05808 -0.0748 0.9238 0.0444
-9.250 -0.5921 0.06392 0.05547 -0.0728 0.9181 0.0442
-9.000 -0.5891 0.06159 0.05274 -0.0711 0.9136 0.0433
-8.750 -0.5879 0.05969 0.05063 -0.0686 0.9079 0.0440
-8.500 -0.5800 0.05750 0.04810 -0.0668 0.9036 0.0438
-8.250 -0.5656 0.05524 0.04540 -0.0656 0.9004 0.0431
-8.000 -0.5595 0.05378 0.04356 -0.0625 0.8957 0.0421
-7.750 -0.5506 0.05300 0.04233 -0.0595 0.8917 0.0409
-7.500 -0.5302 0.05162 0.04057 -0.0584 0.8891 0.0402
-7.250 -0.4923 0.04860 0.03734 -0.0599 0.8880 0.0398
-7.000 -0.2368 0.04353 0.03190 -0.0816 0.9015 0.0442
-6.750 -0.1910 0.04372 0.03201 -0.0816 0.9004 0.0486
-6.500 -0.1707 0.04364 0.03181 -0.0798 0.8973 0.0504
-6.250 -0.1587 0.04334 0.03139 -0.0777 0.8939 0.0518
-6.000 -0.1482 0.04282 0.03071 -0.0760 0.8906 0.0532
-5.750 -0.1427 0.04187 0.02970 -0.0741 0.8874 0.0558
-5.500 -0.1394 0.04121 0.02897 -0.0718 0.8839 0.0602
-5.250 -0.1412 0.04085 0.02853 -0.0684 0.8796 0.0651
-5.000 -0.1428 0.04027 0.02791 -0.0653 0.8763 0.0700
-4.750 -0.1423 0.03964 0.02721 -0.0625 0.8735 0.0760
-4.500 -0.1251 0.04084 0.03088 -0.0568 0.8720 0.4830
-4.250 -0.1495 0.04079 0.03080 -0.0500 0.8668 0.5109
-4.000 -0.1720 0.04059 0.03056 -0.0435 0.8623 0.5339
-3.750 -0.1970 0.04006 0.02998 -0.0369 0.8588 0.5521
-3.500 -0.0689 0.05031 0.03958 -0.0380 0.8610 0.7140
-3.250 -0.0732 0.05009 0.03925 -0.0342 0.8582 0.7184
-3.000 -0.0816 0.05018 0.03927 -0.0291 0.8544 0.7216
-2.750 -0.0833 0.05025 0.03926 -0.0251 0.8511 0.7244
-2.500 -0.0882 0.05018 0.03911 -0.0207 0.8478 0.7278
-2.250 -0.1051 0.04990 0.03878 -0.0145 0.8444 0.7324
-2.000 -0.1176 0.04981 0.03865 -0.0088 0.8409 0.7357
-1.750 -0.1254 0.04975 0.03853 -0.0037 0.8370 0.7385
-1.500 -0.1265 0.04948 0.03818 -0.0001 0.8337 0.7416
-1.250 -0.1294 0.04902 0.03760 0.0036 0.8308 0.7455
-1.000 -0.1353 0.04857 0.03709 0.0078 0.8274 0.7489
-0.750 -0.1370 0.04842 0.03688 0.0117 0.8235 0.7512
-0.500 -0.1295 0.04819 0.03658 0.0139 0.8202 0.7538
-0.250 -0.1178 0.04789 0.03618 0.0153 0.8172 0.7567
0.000 -0.1084 0.04748 0.03566 0.0169 0.8143 0.7596
0.250 -0.1186 0.04706 0.03521 0.0216 0.8093 0.7629
0.500 -0.1031 0.04700 0.03509 0.0226 0.8057 0.7649
0.750 -0.0822 0.04693 0.03496 0.0227 0.8027 0.7670
1.000 -0.0685 0.04681 0.03478 0.0237 0.7990 0.7694
1.250 -0.0648 0.04659 0.03454 0.0261 0.7939 0.7722
1.500 -0.0478 0.04641 0.03429 0.0264 0.7899 0.7750
1.750 -0.0212 0.04646 0.03431 0.0254 0.7869 0.7771
2.000 -0.0162 0.04650 0.03435 0.0279 0.7808 0.7793
2.250 0.0037 0.04657 0.03443 0.0280 0.7764 0.7813
2.500 0.0324 0.04669 0.03454 0.0268 0.7729 0.7832
2.750 0.0388 0.04674 0.03460 0.0287 0.7662 0.7860
3.000 0.0622 0.04683 0.03471 0.0279 0.7613 0.7887
3.250 0.0857 0.04702 0.03493 0.0274 0.7566 0.7909
3.500 0.0993 0.04723 0.03521 0.0285 0.7496 0.7929
3.750 0.1291 0.04746 0.03550 0.0272 0.7452 0.7947
4.000 0.1409 0.04771 0.03581 0.0283 0.7373 0.7971
4.250 0.1687 0.04794 0.03612 0.0272 0.7320 0.7995
4.500 0.1849 0.04822 0.03651 0.0275 0.7240 0.8023
4.750 0.2128 0.04846 0.03685 0.0264 0.7180 0.8047
5.000 0.2283 0.04880 0.03729 0.0272 0.7094 0.8068
5.250 0.2579 0.04902 0.03765 0.0261 0.7033 0.8089
5.500 0.2730 0.04937 0.03812 0.0268 0.6935 0.8113
5.750 0.3079 0.04951 0.03846 0.0251 0.6879 0.8138
6.000 0.3230 0.04985 0.03894 0.0255 0.6768 0.8167
6.250 0.3424 0.05012 0.03937 0.0257 0.6666 0.8193
6.500 0.3770 0.05002 0.03949 0.0246 0.6598 0.8217
6.750 0.3936 0.05023 0.03988 0.0253 0.6476 0.8243
7.000 0.4138 0.05033 0.04022 0.0255 0.6354 0.8271
7.250 0.4365 0.05030 0.04040 0.0254 0.6227 0.8299
7.500 0.4596 0.05012 0.04045 0.0256 0.6094 0.8328
7.750 0.4818 0.04976 0.04035 0.0263 0.5952 0.8357
8.000 0.5070 0.04912 0.04004 0.0268 0.5800 0.8390
8.250 0.5305 0.04844 0.03963 0.0275 0.5621 0.8425
8.500 0.5536 0.04768 0.03915 0.0282 0.5410 0.8460
8.750 0.5775 0.04645 0.03823 0.0297 0.5182 0.8491
9.000 0.6004 0.04513 0.03720 0.0313 0.4896 0.8527
9.250 0.6280 0.04350 0.03587 0.0328 0.4500 0.8567
9.500 0.6636 0.04119 0.03348 0.0347 0.3766 0.8608
9.750 0.6789 0.04108 0.03279 0.0372 0.2888 0.8648
10.000 0.6801 0.04272 0.03399 0.0390 0.2295 0.8692
10.500 0.6847 0.04656 0.03729 0.0415 0.1560 0.8780
10.750 0.6912 0.04836 0.03898 0.0423 0.1319 0.8828
11.000 0.7022 0.05000 0.04055 0.0429 0.1163 0.8878
11.250 0.7167 0.05129 0.04189 0.0438 0.1033 0.8932
11.500 0.7324 0.05266 0.04339 0.0443 0.0905 0.8996
11.750 0.7585 0.05363 0.04461 0.0449 0.0800 0.9063
12.000 0.7817 0.05500 0.04622 0.0452 0.0694 0.9145
12.250 0.8064 0.05669 0.04813 0.0453 0.0603 0.9233
12.500 0.8206 0.05873 0.05028 0.0450 0.0531 0.9348
12.750 0.8353 0.06163 0.05367 0.0447 0.0471 0.9498
13.000 0.8393 0.06396 0.05619 0.0442 0.0431 1.0000
13.250 0.8479 0.06744 0.05985 0.0435 0.0401 1.0000
13.500 0.8469 0.07176 0.06462 0.0428 0.0387 1.0000
13.750 0.8382 0.07653 0.06977 0.0419 0.0373 1.0000
14.000 0.8279 0.08145 0.07501 0.0405 0.0368 1.0000
14.250 0.8126 0.08687 0.08069 0.0386 0.0359 1.0000
14.500 0.7952 0.09309 0.08716 0.0360 0.0363 1.0000
14.750 0.7737 0.10030 0.09459 0.0323 0.0365 1.0000
15.000 0.7511 0.10853 0.10299 0.0275 0.0372 1.0000
15.250 0.7295 0.11764 0.11221 0.0218 0.0380 1.0000
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