NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 200,000 Max Cl/Cd: 85.66 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s802-nr-200000-n5.txt Download as CSV file: xf-s802-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S802 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3590 0.12178 0.11807 -0.0476 1.0000 0.0259
-11.000 -0.3592 0.11824 0.11457 -0.0480 1.0000 0.0259
-10.750 -0.3600 0.11476 0.11113 -0.0483 1.0000 0.0259
-10.500 -0.3569 0.11037 0.10674 -0.0465 1.0000 0.0201
-10.250 -0.3571 0.10779 0.10421 -0.0458 1.0000 0.0198
-10.000 -0.3483 0.10356 0.09999 -0.0488 0.9982 0.0195
-9.750 -0.3376 0.09857 0.09500 -0.0534 0.9951 0.0194
-9.500 -0.3321 0.09208 0.08852 -0.0592 0.9909 0.0199
-9.250 -0.3272 0.08509 0.08154 -0.0659 0.9858 0.0201
-9.000 -0.3200 0.08025 0.07672 -0.0701 0.9790 0.0200
-8.750 -0.3137 0.07503 0.07152 -0.0750 0.9706 0.0197
-8.500 -0.3139 0.06865 0.06516 -0.0810 0.9575 0.0195
-8.250 -0.3200 0.05937 0.05587 -0.0920 0.9401 0.0192
-8.000 -0.3224 0.04764 0.04378 -0.1053 0.9254 0.0188
-7.750 -0.3147 0.03890 0.03447 -0.1127 0.9151 0.0187
-7.500 -0.2959 0.03245 0.02730 -0.1174 0.9071 0.0190
-7.250 -0.2720 0.02823 0.02238 -0.1200 0.8993 0.0197
-7.000 -0.2425 0.02534 0.01892 -0.1224 0.8930 0.0207
-6.750 -0.2119 0.02344 0.01676 -0.1243 0.8869 0.0213
-6.500 -0.1815 0.02181 0.01485 -0.1256 0.8798 0.0218
-6.250 -0.1483 0.02035 0.01311 -0.1273 0.8742 0.0224
-6.000 -0.1197 0.01919 0.01174 -0.1279 0.8662 0.0231
-5.750 -0.0876 0.01811 0.01046 -0.1291 0.8602 0.0239
-5.500 -0.0599 0.01739 0.00956 -0.1293 0.8526 0.0253
-5.250 -0.0302 0.01653 0.00857 -0.1299 0.8465 0.0264
-5.000 -0.0029 0.01577 0.00777 -0.1302 0.8401 0.0273
-4.750 0.0252 0.01518 0.00712 -0.1305 0.8338 0.0283
-4.500 0.0545 0.01466 0.00650 -0.1311 0.8286 0.0297
-4.250 0.0812 0.01423 0.00599 -0.1311 0.8220 0.0313
-4.000 0.1100 0.01381 0.00550 -0.1315 0.8166 0.0341
-3.750 0.1383 0.01349 0.00512 -0.1318 0.8115 0.0385
-3.500 0.1658 0.01313 0.00474 -0.1319 0.8062 0.0450
-3.250 0.1946 0.01275 0.00440 -0.1323 0.8017 0.0651
-3.000 0.2234 0.01236 0.00415 -0.1329 0.7977 0.1115
-2.750 0.2505 0.01196 0.00400 -0.1333 0.7926 0.1816
-2.500 0.2787 0.01141 0.00388 -0.1340 0.7881 0.2979
-2.250 0.3074 0.01077 0.00381 -0.1348 0.7844 0.4632
-2.000 0.3314 0.01048 0.00406 -0.1339 0.7803 0.6118
-1.750 0.3564 0.01058 0.00427 -0.1330 0.7762 0.6810
-1.500 0.3833 0.01071 0.00437 -0.1325 0.7724 0.7151
-1.250 0.4114 0.01084 0.00440 -0.1324 0.7692 0.7362
-1.000 0.4377 0.01096 0.00449 -0.1319 0.7652 0.7525
-0.750 0.4636 0.01107 0.00458 -0.1314 0.7614 0.7658
-0.500 0.4899 0.01118 0.00466 -0.1309 0.7579 0.7775
-0.250 0.5173 0.01128 0.00471 -0.1307 0.7548 0.7885
0.000 0.5441 0.01139 0.00478 -0.1304 0.7515 0.7992
0.250 0.5686 0.01149 0.00490 -0.1295 0.7476 0.8077
0.500 0.5954 0.01158 0.00497 -0.1293 0.7440 0.8167
0.750 0.6213 0.01165 0.00504 -0.1287 0.7406 0.8241
1.000 0.6496 0.01174 0.00509 -0.1288 0.7376 0.8315
1.250 0.6736 0.01181 0.00521 -0.1280 0.7330 0.8371
1.500 0.7007 0.01188 0.00528 -0.1279 0.7285 0.8426
1.750 0.7289 0.01194 0.00531 -0.1280 0.7244 0.8469
2.000 0.7546 0.01200 0.00541 -0.1276 0.7194 0.8507
2.250 0.7807 0.01205 0.00549 -0.1272 0.7135 0.8548
2.500 0.8098 0.01209 0.00549 -0.1275 0.7078 0.8587
2.750 0.8337 0.01213 0.00560 -0.1267 0.6996 0.8623
3.000 0.8609 0.01213 0.00557 -0.1264 0.6922 0.8658
3.250 0.8847 0.01216 0.00567 -0.1256 0.6825 0.8700
3.500 0.9113 0.01220 0.00572 -0.1253 0.6734 0.8741
3.750 0.9361 0.01220 0.00575 -0.1246 0.6631 0.8775
4.000 0.9594 0.01223 0.00584 -0.1237 0.6513 0.8819
4.250 0.9839 0.01227 0.00592 -0.1230 0.6391 0.8866
4.500 1.0077 0.01232 0.00602 -0.1221 0.6256 0.8910
4.750 1.0302 0.01236 0.00611 -0.1210 0.6096 0.8957
5.000 1.0525 0.01243 0.00619 -0.1198 0.5887 0.9017
5.250 1.0724 0.01252 0.00627 -0.1182 0.5591 0.9082
5.500 1.0892 0.01274 0.00634 -0.1159 0.5116 0.9161
5.750 1.0993 0.01326 0.00655 -0.1124 0.4533 0.9272
6.000 1.1072 0.01399 0.00698 -0.1088 0.3947 0.9487
6.250 1.1179 0.01485 0.00756 -0.1061 0.3389 1.0000
6.500 1.1286 0.01576 0.00822 -0.1036 0.2926 1.0000
6.750 1.1394 0.01665 0.00891 -0.1010 0.2528 1.0000
7.000 1.1511 0.01753 0.00962 -0.0987 0.2185 1.0000
7.250 1.1634 0.01840 0.01034 -0.0966 0.1893 1.0000
7.500 1.1763 0.01926 0.01109 -0.0946 0.1650 1.0000
7.750 1.1894 0.02013 0.01186 -0.0926 0.1446 1.0000
8.000 1.2023 0.02101 0.01269 -0.0907 0.1281 1.0000
8.250 1.2155 0.02190 0.01353 -0.0889 0.1140 1.0000
8.500 1.2289 0.02279 0.01440 -0.0872 0.1022 1.0000
8.750 1.2426 0.02368 0.01530 -0.0856 0.0927 1.0000
9.000 1.2552 0.02465 0.01628 -0.0839 0.0846 1.0000
9.250 1.2677 0.02567 0.01731 -0.0823 0.0774 1.0000
9.500 1.2803 0.02670 0.01840 -0.0807 0.0722 1.0000
9.750 1.2926 0.02777 0.01952 -0.0792 0.0670 1.0000
10.000 1.3028 0.02904 0.02079 -0.0775 0.0627 1.0000
10.250 1.3158 0.03012 0.02197 -0.0762 0.0588 1.0000
10.500 1.3268 0.03138 0.02330 -0.0748 0.0554 1.0000
10.750 1.3347 0.03292 0.02486 -0.0732 0.0524 1.0000
11.000 1.3466 0.03418 0.02624 -0.0719 0.0500 1.0000
11.250 1.3578 0.03552 0.02768 -0.0707 0.0473 1.0000
11.500 1.3673 0.03701 0.02924 -0.0695 0.0450 1.0000
11.750 1.3738 0.03883 0.03109 -0.0681 0.0430 1.0000
12.000 1.3834 0.04042 0.03280 -0.0670 0.0413 1.0000
12.250 1.3933 0.04200 0.03453 -0.0659 0.0394 1.0000
12.500 1.4022 0.04368 0.03632 -0.0650 0.0375 1.0000
12.750 1.4096 0.04553 0.03825 -0.0640 0.0360 1.0000
13.000 1.4140 0.04776 0.04052 -0.0630 0.0345 1.0000
13.250 1.4213 0.04973 0.04264 -0.0622 0.0332 1.0000
13.500 1.4289 0.05170 0.04477 -0.0614 0.0317 1.0000
13.750 1.4354 0.05381 0.04701 -0.0608 0.0302 1.0000
14.000 1.4405 0.05608 0.04941 -0.0603 0.0290 1.0000
14.250 1.4432 0.05868 0.05209 -0.0599 0.0278 1.0000
14.500 1.4454 0.06143 0.05496 -0.0595 0.0266 1.0000
14.750 1.4498 0.06401 0.05774 -0.0592 0.0254 1.0000
15.000 1.4525 0.06683 0.06072 -0.0591 0.0241 1.0000
15.250 1.4540 0.06986 0.06389 -0.0592 0.0231 1.0000
15.500 1.4538 0.07316 0.06730 -0.0596 0.0222 1.0000
15.750 1.4504 0.07701 0.07124 -0.0601 0.0214 1.0000
16.000 1.4488 0.08080 0.07522 -0.0607 0.0206 1.0000
16.250 1.4466 0.08479 0.07943 -0.0615 0.0197 1.0000
16.500 1.4431 0.08906 0.08389 -0.0626 0.0189 1.0000
16.750 1.4385 0.09362 0.08863 -0.0641 0.0182 1.0000
17.000 1.4330 0.09849 0.09364 -0.0660 0.0176 1.0000
17.250 1.4259 0.10377 0.09906 -0.0682 0.0171 1.0000
17.500 1.4172 0.10951 0.10492 -0.0708 0.0167 1.0000
17.750 1.4074 0.11561 0.11119 -0.0738 0.0163 1.0000
18.000 1.3970 0.12204 0.11785 -0.0771 0.0159 1.0000
18.250 1.3853 0.12893 0.12495 -0.0809 0.0156 1.0000
18.500 1.3727 0.13621 0.13244 -0.0852 0.0153 1.0000
18.750 1.3591 0.14396 0.14038 -0.0901 0.0150 1.0000
19.000 1.3440 0.15228 0.14888 -0.0955 0.0148 1.0000
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