NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S810 Airfoil (s810-nr) Reynolds number: 200,000 Max Cl/Cd: 50 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s810-nr-200000.txt Download as CSV file: xf-s810-nr-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4696 0.09438 0.09041 -0.0843 0.8826 0.0285
-12.000 -0.4798 0.09078 0.08671 -0.0849 0.8771 0.0284
-11.750 -0.4959 0.08760 0.08337 -0.0850 0.8723 0.0285
-11.500 -0.5128 0.08466 0.08030 -0.0847 0.8674 0.0285
-11.250 -0.5357 0.08239 0.07786 -0.0832 0.8625 0.0285
-11.000 -0.5458 0.07974 0.07507 -0.0820 0.8588 0.0285
-10.750 -0.5647 0.07784 0.07301 -0.0795 0.8551 0.0286
-10.500 -0.5801 0.07605 0.07108 -0.0765 0.8514 0.0286
-10.250 -0.5950 0.06867 0.06360 -0.0754 0.8489 0.0292
-10.000 -0.5776 0.06142 0.05644 -0.0778 0.8473 0.0308
-9.750 -0.5815 0.05913 0.05404 -0.0756 0.8448 0.0313
-9.500 -0.5826 0.05681 0.05158 -0.0737 0.8427 0.0321
-9.250 -0.5823 0.05456 0.04921 -0.0719 0.8404 0.0336
-9.000 -0.5802 0.05279 0.04725 -0.0699 0.8381 0.0361
-8.750 -0.5757 0.05184 0.04602 -0.0673 0.8359 0.0383
-8.500 -0.5533 0.03697 0.03112 -0.0619 0.8310 0.0416
-8.250 -0.5370 0.03302 0.02720 -0.0625 0.8299 0.0437
-8.000 -0.5260 0.03056 0.02462 -0.0614 0.8286 0.0466
-7.750 -0.5165 0.02988 0.02364 -0.0591 0.8269 0.0515
-7.500 -0.5086 0.02643 0.01994 -0.0578 0.8255 0.0555
-7.250 -0.4891 0.02392 0.01744 -0.0580 0.8242 0.0597
-7.000 -0.4804 0.02240 0.01558 -0.0559 0.8227 0.0691
-6.750 -0.4586 0.02030 0.01349 -0.0562 0.8213 0.0763
-6.500 -0.4438 0.01838 0.01143 -0.0555 0.8198 0.0901
-5.500 -0.2958 0.02791 0.01945 -0.0588 0.8173 0.0403
-5.250 -0.1834 0.02505 0.01679 -0.0680 0.8184 0.0385
-5.000 -0.1584 0.02460 0.01637 -0.0669 0.8174 0.0377
-4.750 -0.1440 0.02405 0.01582 -0.0651 0.8163 0.0378
-4.500 -0.1351 0.02338 0.01514 -0.0629 0.8152 0.0385
-4.250 -0.1295 0.02269 0.01445 -0.0607 0.8139 0.0392
-4.000 -0.1270 0.02214 0.01387 -0.0583 0.8122 0.0401
-3.750 -0.1356 0.02169 0.01336 -0.0541 0.8097 0.0411
-3.500 -0.1393 0.02134 0.01292 -0.0504 0.8079 0.0453
-3.250 -0.1310 0.02124 0.01274 -0.0482 0.8064 0.0515
-3.000 -0.1227 0.02098 0.01240 -0.0457 0.8046 0.0645
-2.750 -0.1370 0.01941 0.01165 -0.0407 0.8026 0.3144
-2.500 -0.1339 0.02134 0.01497 -0.0347 0.8015 0.6482
-2.250 0.0367 0.03282 0.02674 -0.0400 0.8038 0.6866
-2.000 -0.0084 0.03087 0.02476 -0.0329 0.8014 0.6897
-1.750 0.0562 0.03238 0.02621 -0.0362 0.8012 0.6951
-1.500 0.0653 0.03260 0.02643 -0.0343 0.7992 0.6976
-1.250 -0.0245 0.03205 0.02596 -0.0209 0.7922 0.7064
-1.000 -0.0058 0.03208 0.02595 -0.0199 0.7903 0.7075
-0.750 0.0170 0.03199 0.02580 -0.0197 0.7888 0.7086
-0.500 0.0419 0.03188 0.02566 -0.0198 0.7876 0.7100
-0.250 -0.0476 0.03291 0.02675 -0.0036 0.7778 0.7153
0.000 -0.0226 0.03238 0.02613 -0.0052 0.7758 0.7178
0.250 0.0145 0.03186 0.02550 -0.0084 0.7743 0.7202
0.500 0.0558 0.03176 0.02538 -0.0109 0.7733 0.7211
0.750 0.0967 0.03162 0.02522 -0.0133 0.7725 0.7220
1.000 0.0402 0.03266 0.02629 -0.0014 0.7616 0.7244
1.250 0.0793 0.03249 0.02610 -0.0039 0.7599 0.7256
1.500 0.1230 0.03229 0.02588 -0.0070 0.7588 0.7269
1.750 0.1012 0.03295 0.02652 -0.0012 0.7486 0.7299
2.000 0.1393 0.03269 0.02623 -0.0038 0.7465 0.7320
2.250 0.1842 0.03234 0.02584 -0.0076 0.7451 0.7338
2.500 0.2282 0.03213 0.02568 -0.0104 0.7441 0.7346
2.750 0.2110 0.03288 0.02646 -0.0045 0.7326 0.7360
3.000 0.2529 0.03260 0.02622 -0.0068 0.7311 0.7371
3.250 0.2964 0.03237 0.02605 -0.0094 0.7299 0.7384
3.500 0.2891 0.03303 0.02675 -0.0052 0.7183 0.7405
3.750 0.3036 0.03338 0.02712 -0.0041 0.7103 0.7424
4.000 0.3360 0.03318 0.02696 -0.0054 0.7059 0.7440
4.250 0.3797 0.03262 0.02646 -0.0081 0.7039 0.7456
4.500 0.4300 0.03186 0.02579 -0.0117 0.7027 0.7472
4.750 0.4825 0.03093 0.02496 -0.0153 0.7012 0.7485
5.000 0.4854 0.03116 0.02526 -0.0118 0.6897 0.7501
5.250 0.4990 0.03123 0.02542 -0.0099 0.6796 0.7517
5.500 0.5604 0.02942 0.02380 -0.0137 0.6781 0.7531
5.750 0.6396 0.02674 0.02129 -0.0197 0.6777 0.7543
6.000 0.7137 0.02395 0.01867 -0.0251 0.6756 0.7557
6.250 0.7518 0.02232 0.01714 -0.0258 0.6642 0.7574
6.500 0.7916 0.02049 0.01541 -0.0268 0.6504 0.7593
6.750 0.8174 0.01955 0.01460 -0.0262 0.6359 0.7614
7.000 0.8324 0.01891 0.01412 -0.0238 0.6173 0.7632
7.250 0.8266 0.01896 0.01433 -0.0182 0.5917 0.7652
7.500 0.8615 0.01723 0.01195 -0.0171 0.4714 0.7669
7.750 0.8443 0.01830 0.01252 -0.0101 0.3957 0.7689
8.000 0.8273 0.01995 0.01376 -0.0045 0.3277 0.7712
8.250 0.8136 0.02181 0.01523 -0.0002 0.2624 0.7734
8.750 0.7972 0.02564 0.01829 0.0063 0.1443 0.7774
9.000 0.7960 0.02730 0.01973 0.0088 0.1099 0.7794
9.250 0.7993 0.02879 0.02109 0.0108 0.0919 0.7815
9.500 0.8070 0.03009 0.02234 0.0122 0.0791 0.7836
9.750 0.8192 0.03114 0.02341 0.0131 0.0685 0.7858
10.000 0.8309 0.03228 0.02456 0.0139 0.0603 0.7881
10.250 0.8410 0.03359 0.02584 0.0147 0.0520 0.7901
10.500 0.8551 0.03447 0.02688 0.0155 0.0456 0.7920
10.750 0.8633 0.03600 0.02846 0.0169 0.0374 0.7940
11.000 0.8711 0.03773 0.03019 0.0182 0.0292 0.7963
11.250 0.8839 0.03898 0.03154 0.0190 0.0245 0.7990
11.500 0.8983 0.04063 0.03321 0.0197 0.0222 0.8017
11.750 0.9232 0.04255 0.03531 0.0202 0.0200 0.8040
12.000 0.9432 0.04423 0.03723 0.0209 0.0189 0.8061
12.250 0.9617 0.04632 0.03960 0.0215 0.0182 0.8084
12.500 0.9753 0.04883 0.04240 0.0223 0.0178 0.8109
12.750 0.9832 0.05176 0.04568 0.0232 0.0176 0.8135
13.000 0.9844 0.05526 0.04950 0.0243 0.0176 0.8161
13.250 0.9786 0.05911 0.05369 0.0254 0.0177 0.8185
13.500 0.9674 0.06313 0.05805 0.0265 0.0179 0.8206
13.750 0.9515 0.06769 0.06292 0.0274 0.0181 0.8229
14.000 0.9343 0.07239 0.06791 0.0276 0.0183 0.8254
14.250 0.9132 0.07780 0.07358 0.0273 0.0185 0.8279
14.500 0.8930 0.08338 0.07939 0.0261 0.0188 0.8305
14.750 0.8700 0.08973 0.08596 0.0241 0.0190 0.8327
15.000 0.8470 0.09651 0.09295 0.0214 0.0192 0.8348
15.250 0.8232 0.10420 0.10083 0.0175 0.0195 0.8370
15.500 0.7998 0.11274 0.10954 0.0125 0.0197 0.8393
15.750 0.7734 0.12326 0.12017 0.0059 0.0200 0.8411
16.000 0.7475 0.13515 0.13213 -0.0014 0.0206 0.8426
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