NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S817 Airfoil (s817-nr) Reynolds number: 100,000 Max Cl/Cd: 26.6 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s817-nr-100000-n5.txt Download as CSV file: xf-s817-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S817 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1504 0.12205 0.11691 -0.0894 0.8602 0.0422
-12.750 -0.1513 0.11924 0.11407 -0.0914 0.8578 0.0424
-12.500 -0.1553 0.11632 0.11118 -0.0941 0.8552 0.0428
-12.250 -0.1576 0.11308 0.10793 -0.0964 0.8526 0.0429
-12.000 -0.1595 0.10962 0.10447 -0.0986 0.8500 0.0430
-11.750 -0.1361 0.10459 0.09941 -0.0958 0.8474 0.0450
-11.500 -0.1314 0.10123 0.09602 -0.0965 0.8452 0.0458
-11.250 -0.1283 0.09780 0.09258 -0.0977 0.8430 0.0467
-11.000 -0.1267 0.09414 0.08893 -0.0990 0.8406 0.0476
-10.750 -0.1259 0.09051 0.08531 -0.1005 0.8383 0.0483
-10.500 -0.1268 0.08656 0.08137 -0.1021 0.8362 0.0491
-10.250 -0.1290 0.08254 0.07736 -0.1038 0.8342 0.0498
-10.000 -0.1322 0.07835 0.07315 -0.1057 0.8324 0.0502
-9.500 -0.1474 0.06895 0.06376 -0.1109 0.8288 0.0505
-8.000 -0.2716 0.05944 0.05324 -0.1095 0.8176 0.0308
-7.750 -0.2764 0.05562 0.04895 -0.1058 0.8152 0.0240
-7.500 -0.2739 0.05296 0.04623 -0.1041 0.8122 0.0234
-7.250 -0.2707 0.05054 0.04365 -0.1020 0.8094 0.0228
-7.000 -0.2652 0.04819 0.04109 -0.0998 0.8071 0.0221
-6.750 -0.2578 0.04571 0.03834 -0.0975 0.8050 0.0215
-6.500 -0.2478 0.04321 0.03552 -0.0953 0.8032 0.0209
-6.250 -0.2348 0.04073 0.03268 -0.0932 0.8016 0.0204
-6.000 -0.2207 0.03843 0.03003 -0.0911 0.7998 0.0200
-5.750 -0.2072 0.03654 0.02784 -0.0889 0.7970 0.0199
-5.500 -0.1901 0.03469 0.02566 -0.0870 0.7945 0.0199
-5.250 -0.1691 0.03292 0.02358 -0.0858 0.7925 0.0201
-5.000 -0.1461 0.03156 0.02194 -0.0849 0.7910 0.0221
-4.750 -0.1190 0.03023 0.02022 -0.0844 0.7897 0.0241
-4.500 -0.0903 0.02865 0.01856 -0.0846 0.7886 0.0257
-4.250 -0.0615 0.02750 0.01734 -0.0847 0.7876 0.0277
-4.000 -0.0344 0.02678 0.01648 -0.0845 0.7866 0.0321
-3.750 -0.0214 0.02629 0.01608 -0.0822 0.7839 0.0355
-3.500 -0.0124 0.02614 0.01593 -0.0791 0.7808 0.0388
-3.250 -0.0015 0.02600 0.01575 -0.0763 0.7784 0.0452
-3.000 0.0101 0.02584 0.01555 -0.0737 0.7765 0.0514
-2.750 0.0226 0.02562 0.01527 -0.0712 0.7747 0.0626
-2.500 0.0364 0.02524 0.01489 -0.0690 0.7731 0.0865
-2.250 0.0370 0.02481 0.01482 -0.0650 0.7704 0.1607
-2.000 0.0106 0.02465 0.01545 -0.0573 0.7647 0.3509
-1.750 0.0022 0.02515 0.01719 -0.0491 0.7617 0.7150
-1.500 0.0156 0.02651 0.01850 -0.0441 0.7599 0.7626
-1.250 0.0329 0.02755 0.01945 -0.0402 0.7586 0.7898
-0.750 0.0160 0.02943 0.02130 -0.0279 0.7492 0.8120
-0.500 0.0290 0.03003 0.02182 -0.0245 0.7469 0.8257
-0.250 0.0483 0.03023 0.02187 -0.0234 0.7453 0.8317
0.000 0.0740 0.03028 0.02178 -0.0237 0.7441 0.8328
0.250 0.1026 0.03029 0.02165 -0.0245 0.7430 0.8336
0.750 0.1044 0.03163 0.02292 -0.0182 0.7332 0.8383
1.250 0.1578 0.03187 0.02296 -0.0193 0.7299 0.8415
1.500 0.1863 0.03200 0.02301 -0.0202 0.7288 0.8430
1.750 0.1812 0.03298 0.02399 -0.0165 0.7219 0.8456
2.000 0.2017 0.03333 0.02430 -0.0162 0.7191 0.8470
2.250 0.2275 0.03354 0.02447 -0.0165 0.7170 0.8484
2.500 0.2560 0.03370 0.02461 -0.0173 0.7154 0.8497
2.750 0.2860 0.03384 0.02473 -0.0183 0.7142 0.8511
3.000 0.2820 0.03490 0.02582 -0.0149 0.7063 0.8545
3.250 0.3067 0.03520 0.02611 -0.0152 0.7036 0.8568
3.750 0.3653 0.03553 0.02650 -0.0169 0.7001 0.8606
4.000 0.3644 0.03653 0.02754 -0.0138 0.6920 0.8636
4.250 0.3892 0.03682 0.02788 -0.0141 0.6890 0.8658
4.500 0.4189 0.03698 0.02807 -0.0150 0.6869 0.8680
4.750 0.4508 0.03709 0.02825 -0.0161 0.6854 0.8702
5.000 0.4511 0.03814 0.02939 -0.0136 0.6760 0.8738
5.250 0.4791 0.03828 0.02961 -0.0141 0.6733 0.8761
5.500 0.5107 0.03831 0.02974 -0.0150 0.6715 0.8785
5.750 0.5135 0.03925 0.03076 -0.0126 0.6619 0.8828
6.000 0.5436 0.03931 0.03095 -0.0134 0.6590 0.8862
6.250 0.5766 0.03919 0.03096 -0.0144 0.6570 0.8892
6.500 0.5801 0.04004 0.03193 -0.0120 0.6466 0.8940
6.750 0.6131 0.03982 0.03186 -0.0128 0.6439 0.8977
7.000 0.6223 0.04045 0.03265 -0.0112 0.6336 0.9029
7.250 0.6581 0.03979 0.03218 -0.0120 0.6302 0.9066
7.500 0.6797 0.03910 0.03164 -0.0109 0.6175 0.9121
8.000 0.7216 0.03723 0.03012 -0.0081 0.5835 0.9255
8.250 0.7400 0.03702 0.03011 -0.0071 0.5669 0.9345
8.500 0.7627 0.03657 0.02987 -0.0066 0.5476 0.9457
8.750 0.7827 0.03661 0.03012 -0.0065 0.5174 0.9619
9.250 0.8547 0.03213 0.02431 -0.0043 0.2843 1.0000
9.500 0.8524 0.03415 0.02580 -0.0022 0.2067 1.0000
9.750 0.8582 0.03579 0.02706 -0.0009 0.1520 1.0000
10.000 0.8676 0.03724 0.02828 0.0000 0.1187 1.0000
10.250 0.8796 0.03855 0.02951 0.0007 0.0984 1.0000
10.500 0.8916 0.03988 0.03081 0.0014 0.0859 1.0000
10.750 0.9033 0.04127 0.03218 0.0022 0.0765 1.0000
11.000 0.9155 0.04262 0.03356 0.0028 0.0688 1.0000
11.250 0.9283 0.04398 0.03498 0.0035 0.0633 1.0000
11.500 0.9422 0.04527 0.03635 0.0041 0.0584 1.0000
11.750 0.9553 0.04670 0.03779 0.0048 0.0540 1.0000
12.000 0.9724 0.04788 0.03914 0.0052 0.0497 1.0000
12.250 0.9888 0.04919 0.04052 0.0057 0.0463 1.0000
12.500 1.0061 0.05059 0.04193 0.0061 0.0430 1.0000
12.750 1.0248 0.05198 0.04358 0.0064 0.0395 1.0000
13.000 1.0418 0.05352 0.04528 0.0068 0.0368 1.0000
13.250 1.0549 0.05530 0.04709 0.0070 0.0342 1.0000
13.500 1.0718 0.05735 0.04945 0.0075 0.0318 1.0000
13.750 1.0833 0.05969 0.05211 0.0081 0.0294 1.0000
14.000 1.0880 0.06197 0.05457 0.0086 0.0274 1.0000
14.250 1.0928 0.06434 0.05700 0.0090 0.0258 1.0000
14.500 1.0961 0.06771 0.06066 0.0096 0.0246 1.0000
14.750 1.0906 0.07156 0.06494 0.0103 0.0232 1.0000
15.000 1.0836 0.07538 0.06908 0.0107 0.0219 1.0000
15.250 1.0758 0.07918 0.07312 0.0107 0.0208 1.0000
15.500 1.0684 0.08301 0.07715 0.0104 0.0200 1.0000
15.750 1.0603 0.08705 0.08134 0.0098 0.0193 1.0000
16.000 1.0527 0.09119 0.08560 0.0089 0.0187 1.0000
16.250 1.0370 0.09692 0.09154 0.0075 0.0183 1.0000
16.500 1.0175 0.10354 0.09846 0.0052 0.0182 1.0000
16.750 0.9972 0.11074 0.10591 0.0022 0.0181 1.0000
17.000 0.9778 0.11834 0.11372 -0.0016 0.0182 1.0000
17.250 0.9581 0.12663 0.12218 -0.0063 0.0183 1.0000
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