NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 1,000,000 Max Cl/Cd: 149.48 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s802-nr-1000000.txt Download as CSV file: xf-s802-nr-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2965 0.08924 0.08758 -0.0672 0.9914 0.0132
-9.500 -0.2838 0.08522 0.08357 -0.0715 0.9890 0.0140
-9.000 -0.3974 0.03181 0.02932 -0.1206 0.9490 0.0118
-8.750 -0.3793 0.02442 0.02112 -0.1277 0.9380 0.0121
-8.500 -0.3453 0.02040 0.01670 -0.1330 0.9301 0.0127
-8.250 -0.3065 0.01946 0.01566 -0.1366 0.9200 0.0132
-8.000 -0.2748 0.01833 0.01432 -0.1385 0.9048 0.0136
-7.750 -0.2488 0.01723 0.01299 -0.1389 0.8881 0.0141
-7.500 -0.2240 0.01651 0.01205 -0.1389 0.8729 0.0147
-7.250 -0.1998 0.01571 0.01103 -0.1386 0.8591 0.0151
-7.000 -0.1754 0.01504 0.01016 -0.1383 0.8467 0.0154
-6.750 -0.1498 0.01471 0.00968 -0.1380 0.8356 0.0157
-6.500 -0.1270 0.01316 0.00790 -0.1376 0.8254 0.0160
-6.250 -0.1033 0.01201 0.00661 -0.1372 0.8159 0.0165
-6.000 -0.0779 0.01139 0.00594 -0.1370 0.8075 0.0170
-5.750 -0.0518 0.01104 0.00552 -0.1369 0.7998 0.0177
-5.500 -0.0252 0.01067 0.00510 -0.1368 0.7929 0.0184
-5.250 0.0014 0.01029 0.00463 -0.1367 0.7862 0.0189
-5.000 0.0283 0.00991 0.00420 -0.1367 0.7803 0.0193
-4.750 0.0556 0.00961 0.00383 -0.1367 0.7743 0.0198
-4.500 0.0829 0.00936 0.00350 -0.1367 0.7688 0.0201
-4.250 0.1106 0.00900 0.00310 -0.1369 0.7638 0.0206
-4.000 0.1384 0.00862 0.00266 -0.1371 0.7588 0.0219
-3.750 0.1663 0.00844 0.00243 -0.1372 0.7543 0.0234
-3.500 0.1947 0.00827 0.00223 -0.1374 0.7502 0.0246
-3.250 0.2231 0.00813 0.00206 -0.1375 0.7461 0.0258
-3.000 0.2514 0.00796 0.00187 -0.1377 0.7422 0.0300
-2.750 0.2799 0.00768 0.00172 -0.1381 0.7382 0.0686
-2.500 0.3086 0.00734 0.00161 -0.1386 0.7348 0.1372
-2.250 0.3373 0.00704 0.00154 -0.1391 0.7313 0.2095
-2.000 0.3662 0.00672 0.00148 -0.1397 0.7280 0.2998
-1.750 0.3953 0.00646 0.00144 -0.1402 0.7248 0.3895
-1.500 0.4247 0.00610 0.00141 -0.1410 0.7217 0.5126
-1.250 0.4536 0.00579 0.00147 -0.1415 0.7188 0.6375
-1.000 0.4821 0.00577 0.00154 -0.1416 0.7157 0.6861
-0.750 0.5105 0.00582 0.00161 -0.1416 0.7127 0.7134
-0.500 0.5388 0.00591 0.00167 -0.1417 0.7095 0.7282
-0.250 0.5674 0.00598 0.00172 -0.1418 0.7060 0.7372
0.000 0.5954 0.00600 0.00176 -0.1417 0.7021 0.7447
0.250 0.6235 0.00605 0.00179 -0.1418 0.6978 0.7519
0.500 0.6515 0.00613 0.00183 -0.1418 0.6932 0.7578
0.750 0.6792 0.00616 0.00188 -0.1417 0.6885 0.7635
1.000 0.7071 0.00620 0.00191 -0.1417 0.6832 0.7691
1.250 0.7345 0.00627 0.00195 -0.1415 0.6776 0.7739
1.500 0.7620 0.00629 0.00201 -0.1414 0.6725 0.7789
1.750 0.7897 0.00634 0.00205 -0.1414 0.6669 0.7838
2.000 0.8169 0.00641 0.00210 -0.1413 0.6609 0.7880
2.250 0.8442 0.00642 0.00215 -0.1411 0.6544 0.7926
2.500 0.8712 0.00651 0.00222 -0.1409 0.6480 0.7972
2.750 0.8989 0.00655 0.00228 -0.1409 0.6413 0.8007
3.000 0.9257 0.00659 0.00232 -0.1407 0.6339 0.8037
3.250 0.9527 0.00663 0.00239 -0.1405 0.6247 0.8062
3.500 0.9792 0.00671 0.00246 -0.1403 0.6156 0.8088
3.750 1.0057 0.00679 0.00253 -0.1400 0.6031 0.8114
4.000 1.0314 0.00690 0.00260 -0.1396 0.5855 0.8139
4.250 1.0556 0.00708 0.00270 -0.1389 0.5576 0.8163
4.500 1.0762 0.00744 0.00288 -0.1376 0.5090 0.8189
4.750 1.0921 0.00815 0.00326 -0.1354 0.4391 0.8216
5.000 1.1093 0.00884 0.00365 -0.1335 0.3783 0.8245
5.250 1.1274 0.00946 0.00403 -0.1319 0.3250 0.8276
5.500 1.1448 0.01013 0.00443 -0.1301 0.2743 0.8305
5.750 1.1628 0.01069 0.00481 -0.1284 0.2325 0.8335
6.000 1.1808 0.01124 0.00519 -0.1268 0.1972 0.8365
6.250 1.1995 0.01175 0.00557 -0.1253 0.1686 0.8400
6.500 1.2186 0.01222 0.00593 -0.1238 0.1454 0.8437
6.750 1.2374 0.01267 0.00630 -0.1223 0.1264 0.8474
7.000 1.2559 0.01309 0.00667 -0.1207 0.1104 0.8514
7.250 1.2729 0.01350 0.00704 -0.1188 0.0968 0.8558
7.500 1.2896 0.01393 0.00742 -0.1169 0.0858 0.8606
7.750 1.3055 0.01436 0.00783 -0.1148 0.0762 0.8659
8.000 1.3230 0.01475 0.00823 -0.1131 0.0693 0.8720
8.250 1.3387 0.01520 0.00868 -0.1111 0.0621 0.8791
8.500 1.3549 0.01563 0.00913 -0.1092 0.0571 0.8881
8.750 1.3695 0.01610 0.00964 -0.1070 0.0518 0.9003
9.000 1.3834 0.01641 0.01006 -0.1046 0.0490 0.9254
9.250 1.3967 0.01689 0.01057 -0.1023 0.0450 1.0000
9.500 1.4127 0.01748 0.01119 -0.1006 0.0419 1.0000
9.750 1.4298 0.01800 0.01175 -0.0992 0.0399 1.0000
10.000 1.4446 0.01865 0.01239 -0.0975 0.0372 1.0000
10.250 1.4570 0.01947 0.01322 -0.0954 0.0341 1.0000
10.500 1.4743 0.01999 0.01377 -0.0941 0.0327 1.0000
10.750 1.4892 0.02066 0.01448 -0.0926 0.0310 1.0000
11.000 1.5024 0.02147 0.01530 -0.0908 0.0291 1.0000
11.250 1.5121 0.02254 0.01641 -0.0887 0.0271 1.0000
11.500 1.5276 0.02323 0.01715 -0.0874 0.0264 1.0000
11.750 1.5419 0.02401 0.01798 -0.0860 0.0254 1.0000
12.000 1.5551 0.02490 0.01890 -0.0846 0.0242 1.0000
12.250 1.5665 0.02594 0.01996 -0.0830 0.0228 1.0000
12.500 1.5742 0.02732 0.02138 -0.0811 0.0212 1.0000
12.750 1.5883 0.02820 0.02233 -0.0800 0.0206 1.0000
13.000 1.6011 0.02920 0.02339 -0.0788 0.0197 1.0000
13.250 1.6125 0.03034 0.02458 -0.0775 0.0187 1.0000
13.500 1.6221 0.03168 0.02594 -0.0762 0.0176 1.0000
13.750 1.6281 0.03336 0.02768 -0.0746 0.0164 1.0000
14.000 1.6404 0.03450 0.02888 -0.0737 0.0158 1.0000
14.250 1.6509 0.03582 0.03026 -0.0726 0.0149 1.0000
14.500 1.6595 0.03735 0.03184 -0.0716 0.0139 1.0000
14.750 1.6633 0.03941 0.03394 -0.0703 0.0128 1.0000
15.000 1.6732 0.04088 0.03549 -0.0694 0.0121 1.0000
15.250 1.6807 0.04262 0.03729 -0.0686 0.0111 1.0000
15.500 1.6844 0.04483 0.03954 -0.0676 0.0101 1.0000
15.750 1.6889 0.04700 0.04179 -0.0668 0.0094 1.0000
16.000 1.6936 0.04919 0.04406 -0.0661 0.0086 1.0000
16.250 1.6957 0.05173 0.04666 -0.0655 0.0080 1.0000
16.500 1.6923 0.05503 0.05005 -0.0649 0.0073 1.0000
16.750 1.6953 0.05764 0.05277 -0.0645 0.0071 1.0000
17.000 1.6966 0.06052 0.05575 -0.0643 0.0067 1.0000
17.250 1.6962 0.06368 0.05902 -0.0643 0.0064 1.0000
17.500 1.6941 0.06718 0.06262 -0.0644 0.0062 1.0000
17.750 1.6904 0.07102 0.06656 -0.0647 0.0059 1.0000
18.000 1.6832 0.07549 0.07115 -0.0654 0.0057 1.0000
18.250 1.6720 0.08076 0.07655 -0.0665 0.0055 1.0000
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