NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 500,000 Max Cl/Cd: 124.33 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s802-nr-500000.txt Download as CSV file: xf-s802-nr-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3050 0.09008 0.08786 -0.0614 0.9913 0.0225
-9.000 -0.2923 0.08520 0.08298 -0.0668 0.9880 0.0236
-8.250 -0.3002 0.05053 0.04808 -0.1104 0.9528 0.0264
-8.000 -0.2777 0.04854 0.04610 -0.1131 0.9482 0.0269
-7.750 -0.2588 0.04532 0.04277 -0.1170 0.9385 0.0275
-7.500 -0.2284 0.04144 0.03872 -0.1236 0.9339 0.0290
-7.250 -0.2079 0.03253 0.02892 -0.1321 0.9211 0.0335
-7.000 -0.1760 0.03104 0.02749 -0.1346 0.9122 0.0347
-6.750 -0.1568 0.02121 0.01642 -0.1366 0.8980 0.0247
-6.500 -0.1293 0.01843 0.01320 -0.1376 0.8873 0.0240
-6.250 -0.1021 0.01666 0.01110 -0.1379 0.8767 0.0238
-6.000 -0.0756 0.01564 0.00985 -0.1379 0.8664 0.0245
-5.750 -0.0481 0.01478 0.00879 -0.1379 0.8576 0.0251
-5.500 -0.0220 0.01394 0.00779 -0.1377 0.8485 0.0255
-5.250 0.0048 0.01332 0.00703 -0.1376 0.8406 0.0258
-5.000 0.0305 0.01245 0.00606 -0.1373 0.8330 0.0262
-4.750 0.0566 0.01164 0.00518 -0.1373 0.8264 0.0271
-4.500 0.0831 0.01117 0.00468 -0.1372 0.8197 0.0283
-4.000 0.1381 0.01053 0.00392 -0.1374 0.8081 0.0313
-3.750 0.1660 0.01027 0.00358 -0.1375 0.8026 0.0325
-3.500 0.1944 0.00991 0.00317 -0.1378 0.7978 0.0360
-3.250 0.2221 0.00969 0.00293 -0.1378 0.7927 0.0417
-3.000 0.2503 0.00912 0.00266 -0.1383 0.7882 0.1119
-2.750 0.2792 0.00871 0.00252 -0.1390 0.7843 0.2050
-2.500 0.3074 0.00832 0.00244 -0.1396 0.7801 0.3023
-2.250 0.3359 0.00784 0.00237 -0.1403 0.7758 0.4336
-2.000 0.3644 0.00737 0.00238 -0.1408 0.7720 0.5887
-1.750 0.3922 0.00739 0.00259 -0.1407 0.7686 0.6865
-1.500 0.4197 0.00748 0.00270 -0.1405 0.7651 0.7166
-1.250 0.4474 0.00760 0.00280 -0.1403 0.7614 0.7388
-1.000 0.4748 0.00772 0.00292 -0.1400 0.7579 0.7558
-0.750 0.5027 0.00784 0.00300 -0.1398 0.7548 0.7662
-0.500 0.5304 0.00795 0.00309 -0.1397 0.7517 0.7749
-0.250 0.5578 0.00804 0.00318 -0.1396 0.7482 0.7840
0.000 0.5848 0.00810 0.00325 -0.1393 0.7446 0.7908
0.250 0.6128 0.00820 0.00331 -0.1393 0.7412 0.7986
0.500 0.6406 0.00830 0.00339 -0.1391 0.7377 0.8047
0.750 0.6668 0.00835 0.00347 -0.1387 0.7334 0.8114
1.000 0.6941 0.00840 0.00352 -0.1386 0.7289 0.8175
1.250 0.7211 0.00846 0.00356 -0.1383 0.7244 0.8229
1.500 0.7481 0.00852 0.00363 -0.1380 0.7190 0.8289
1.750 0.7741 0.00852 0.00365 -0.1376 0.7129 0.8338
2.000 0.8013 0.00859 0.00368 -0.1373 0.7072 0.8384
2.250 0.8274 0.00859 0.00372 -0.1370 0.7006 0.8430
2.500 0.8549 0.00861 0.00373 -0.1369 0.6943 0.8464
2.750 0.8806 0.00862 0.00376 -0.1364 0.6872 0.8494
3.000 0.9070 0.00863 0.00378 -0.1361 0.6800 0.8526
3.250 0.9337 0.00866 0.00383 -0.1358 0.6728 0.8558
3.500 0.9605 0.00869 0.00387 -0.1357 0.6650 0.8590
3.750 0.9864 0.00870 0.00392 -0.1353 0.6565 0.8618
4.000 1.0119 0.00874 0.00395 -0.1347 0.6471 0.8646
4.250 1.0369 0.00875 0.00403 -0.1342 0.6364 0.8680
4.500 1.0621 0.00880 0.00410 -0.1336 0.6236 0.8714
5.000 1.1093 0.00894 0.00423 -0.1319 0.5871 0.8780
5.250 1.1302 0.00909 0.00434 -0.1305 0.5543 0.8821
5.500 1.1447 0.00958 0.00455 -0.1279 0.4925 0.8867
5.750 1.1550 0.01037 0.00500 -0.1247 0.4247 0.8914
6.000 1.1659 0.01117 0.00550 -0.1217 0.3639 0.8969
6.250 1.1774 0.01199 0.00604 -0.1189 0.3061 0.9034
6.500 1.1883 0.01269 0.00654 -0.1159 0.2598 0.9106
6.750 1.1996 0.01334 0.00701 -0.1131 0.2209 0.9193
7.000 1.2083 0.01389 0.00745 -0.1097 0.1896 0.9337
7.250 1.2202 0.01443 0.00790 -0.1070 0.1622 1.0000
7.500 1.2364 0.01514 0.00849 -0.1054 0.1385 1.0000
7.750 1.2525 0.01583 0.00908 -0.1038 0.1194 1.0000
8.000 1.2680 0.01654 0.00970 -0.1020 0.1039 1.0000
8.250 1.2834 0.01723 0.01034 -0.1003 0.0917 1.0000
8.500 1.2988 0.01791 0.01100 -0.0986 0.0821 1.0000
8.750 1.3123 0.01871 0.01177 -0.0966 0.0741 1.0000
9.000 1.3275 0.01940 0.01247 -0.0950 0.0681 1.0000
9.250 1.3393 0.02031 0.01338 -0.0928 0.0624 1.0000
9.500 1.3548 0.02100 0.01412 -0.0913 0.0584 1.0000
9.750 1.3658 0.02200 0.01510 -0.0893 0.0543 1.0000
10.000 1.3769 0.02303 0.01619 -0.0873 0.0512 1.0000
10.250 1.3915 0.02383 0.01705 -0.0858 0.0485 1.0000
10.500 1.4037 0.02482 0.01807 -0.0842 0.0458 1.0000
10.750 1.4088 0.02638 0.01965 -0.0818 0.0431 1.0000
11.000 1.4211 0.02744 0.02080 -0.0803 0.0416 1.0000
11.250 1.4345 0.02842 0.02187 -0.0790 0.0397 1.0000
11.500 1.4473 0.02948 0.02298 -0.0778 0.0378 1.0000
11.750 1.4560 0.03089 0.02441 -0.0762 0.0358 1.0000
12.000 1.4604 0.03275 0.02633 -0.0744 0.0339 1.0000
12.250 1.4755 0.03367 0.02734 -0.0735 0.0324 1.0000
12.500 1.4874 0.03489 0.02864 -0.0725 0.0309 1.0000
12.750 1.4980 0.03624 0.03003 -0.0714 0.0294 1.0000
13.000 1.5029 0.03818 0.03201 -0.0701 0.0280 1.0000
13.250 1.5058 0.04038 0.03431 -0.0686 0.0268 1.0000
13.500 1.5170 0.04178 0.03583 -0.0678 0.0259 1.0000
13.750 1.5264 0.04338 0.03752 -0.0670 0.0247 1.0000
14.000 1.5354 0.04505 0.03926 -0.0663 0.0235 1.0000
14.250 1.5408 0.04713 0.04138 -0.0655 0.0223 1.0000
14.500 1.5372 0.05028 0.04462 -0.0644 0.0211 1.0000
14.750 1.5472 0.05198 0.04644 -0.0640 0.0202 1.0000
15.000 1.5549 0.05396 0.04853 -0.0636 0.0191 1.0000
15.250 1.5612 0.05615 0.05079 -0.0633 0.0181 1.0000
15.500 1.5612 0.05917 0.05387 -0.0630 0.0171 1.0000
15.750 1.5565 0.06288 0.05771 -0.0627 0.0163 1.0000
16.000 1.5611 0.06551 0.06048 -0.0627 0.0154 1.0000
16.250 1.5632 0.06853 0.06362 -0.0629 0.0146 1.0000
16.500 1.5636 0.07185 0.06703 -0.0633 0.0139 1.0000
16.750 1.5587 0.07603 0.07129 -0.0639 0.0133 1.0000
17.000 1.5457 0.08158 0.07695 -0.0650 0.0127 1.0000
17.250 1.5439 0.08564 0.08118 -0.0660 0.0123 1.0000
17.500 1.5391 0.09027 0.08598 -0.0674 0.0118 1.0000
17.750 1.5332 0.09523 0.09108 -0.0691 0.0114 1.0000
18.000 1.5265 0.10045 0.09642 -0.0711 0.0111 1.0000
18.250 1.5186 0.10604 0.10214 -0.0735 0.0107 1.0000
18.500 1.5093 0.11202 0.10824 -0.0762 0.0105 1.0000
18.750 1.4976 0.11857 0.11492 -0.0795 0.0103 1.0000
19.000 1.4842 0.12554 0.12201 -0.0832 0.0101 1.0000
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