NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S821 Airfoil (s821-nr) Reynolds number: 200,000 Max Cl/Cd: 51.07 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s821-nr-200000-n5.txt Download as CSV file: xf-s821-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S821 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1334 0.09492 0.08917 -0.0597 0.9680 0.1870
-7.000 -0.6132 0.03174 0.02434 -0.0879 0.9111 0.2191
-6.750 -0.5989 0.03064 0.02324 -0.0878 0.9008 0.2200
-6.500 -0.5739 0.02971 0.02236 -0.0889 0.8936 0.2209
-6.250 -0.5532 0.02866 0.02131 -0.0898 0.8847 0.2218
-6.000 -0.5287 0.02760 0.02024 -0.0914 0.8762 0.2229
-5.750 -0.4942 0.02656 0.01918 -0.0945 0.8715 0.2241
-5.500 -0.4723 0.02564 0.01822 -0.0953 0.8600 0.2252
-5.250 -0.4363 0.02466 0.01719 -0.0984 0.8540 0.2265
-5.000 -0.4032 0.02376 0.01622 -0.1008 0.8456 0.2278
-4.750 -0.3671 0.02290 0.01528 -0.1037 0.8367 0.2291
-4.500 -0.3194 0.02202 0.01430 -0.1087 0.8303 0.2306
-4.250 -0.2841 0.02133 0.01350 -0.1112 0.8183 0.2318
-4.000 -0.2379 0.02070 0.01281 -0.1153 0.8091 0.2331
-3.750 -0.2045 0.02034 0.01247 -0.1167 0.7958 0.2343
-3.500 -0.1650 0.02000 0.01212 -0.1192 0.7839 0.2358
-3.250 -0.1339 0.01970 0.01180 -0.1202 0.7699 0.2371
-3.000 -0.1019 0.01941 0.01146 -0.1213 0.7568 0.2386
-2.750 -0.0713 0.01913 0.01112 -0.1222 0.7435 0.2401
-2.500 -0.0430 0.01885 0.01079 -0.1226 0.7305 0.2415
-2.250 -0.0131 0.01859 0.01042 -0.1233 0.7177 0.2431
-2.000 0.0139 0.01833 0.01010 -0.1235 0.7051 0.2446
-1.750 0.0433 0.01810 0.00976 -0.1241 0.6938 0.2460
-1.500 0.0698 0.01788 0.00954 -0.1240 0.6821 0.2474
-1.250 0.0980 0.01774 0.00938 -0.1241 0.6707 0.2489
-1.000 0.1246 0.01761 0.00928 -0.1240 0.6591 0.2504
-0.750 0.1528 0.01751 0.00915 -0.1241 0.6483 0.2522
-0.500 0.1804 0.01740 0.00904 -0.1241 0.6382 0.2542
-0.250 0.2083 0.01729 0.00890 -0.1241 0.6280 0.2563
0.000 0.2366 0.01719 0.00875 -0.1242 0.6184 0.2585
0.250 0.2643 0.01708 0.00859 -0.1242 0.6079 0.2604
0.500 0.2926 0.01700 0.00846 -0.1243 0.5986 0.2623
0.750 0.3198 0.01690 0.00845 -0.1241 0.5891 0.2642
1.000 0.3478 0.01687 0.00842 -0.1240 0.5803 0.2663
1.250 0.3760 0.01684 0.00840 -0.1240 0.5718 0.2686
1.500 0.4037 0.01681 0.00838 -0.1239 0.5625 0.2710
1.750 0.4321 0.01681 0.00832 -0.1239 0.5541 0.2737
2.000 0.4603 0.01678 0.00829 -0.1238 0.5461 0.2765
2.250 0.4881 0.01677 0.00832 -0.1237 0.5377 0.2792
2.500 0.5163 0.01681 0.00838 -0.1236 0.5300 0.2820
2.750 0.5439 0.01682 0.00846 -0.1234 0.5219 0.2850
3.000 0.5717 0.01687 0.00850 -0.1232 0.5139 0.2883
3.250 0.5995 0.01693 0.00853 -0.1230 0.5061 0.2916
3.500 0.6263 0.01695 0.00858 -0.1226 0.4967 0.2946
3.750 0.6528 0.01702 0.00867 -0.1221 0.4875 0.2976
4.000 0.6791 0.01708 0.00879 -0.1216 0.4781 0.3008
4.250 0.7048 0.01717 0.00889 -0.1210 0.4682 0.3044
4.500 0.7307 0.01727 0.00898 -0.1204 0.4590 0.3084
4.750 0.7561 0.01737 0.00908 -0.1197 0.4490 0.3121
5.000 0.7811 0.01749 0.00924 -0.1189 0.4400 0.3159
5.250 0.8057 0.01760 0.00942 -0.1181 0.4296 0.3199
5.500 0.8292 0.01778 0.00956 -0.1171 0.4198 0.3242
5.750 0.8531 0.01790 0.00971 -0.1161 0.4092 0.3284
6.000 0.8746 0.01807 0.00987 -0.1147 0.3991 0.3320
6.250 0.8972 0.01820 0.01010 -0.1135 0.3884 0.3359
6.500 0.9171 0.01842 0.01032 -0.1119 0.3779 0.3401
6.750 0.9384 0.01862 0.01055 -0.1105 0.3658 0.3449
7.000 0.9581 0.01889 0.01078 -0.1089 0.3539 0.3494
7.250 0.9771 0.01918 0.01112 -0.1072 0.3402 0.3536
7.500 0.9964 0.01951 0.01149 -0.1056 0.3252 0.3583
7.750 1.0141 0.01991 0.01187 -0.1038 0.3089 0.3631
8.000 1.0300 0.02039 0.01229 -0.1018 0.2904 0.3679
8.250 1.0442 0.02094 0.01280 -0.0996 0.2701 0.3723
8.500 1.0565 0.02161 0.01342 -0.0973 0.2492 0.3766
8.750 1.0672 0.02239 0.01413 -0.0948 0.2296 0.3814
9.000 1.0777 0.02324 0.01490 -0.0924 0.2117 0.3863
9.250 1.0882 0.02413 0.01571 -0.0902 0.1958 0.3911
9.500 1.0990 0.02504 0.01662 -0.0880 0.1813 0.3956
9.750 1.1096 0.02599 0.01758 -0.0860 0.1684 0.4004
10.000 1.1196 0.02702 0.01859 -0.0840 0.1569 0.4056
10.250 1.1292 0.02812 0.01967 -0.0821 0.1467 0.4108
10.500 1.1377 0.02933 0.02087 -0.0802 0.1374 0.4154
10.750 1.1470 0.03055 0.02213 -0.0786 0.1287 0.4204
11.000 1.1560 0.03183 0.02345 -0.0770 0.1211 0.4258
11.250 1.1634 0.03329 0.02491 -0.0755 0.1143 0.4312
11.750 1.1796 0.03630 0.02801 -0.0730 0.1023 0.4414
12.000 1.1860 0.03803 0.02978 -0.0718 0.0971 0.4469
12.250 1.1938 0.03973 0.03154 -0.0709 0.0924 0.4528
12.500 1.1992 0.04171 0.03353 -0.0700 0.0881 0.4584
12.750 1.2066 0.04358 0.03549 -0.0693 0.0841 0.4636
13.000 1.2116 0.04574 0.03772 -0.0687 0.0803 0.4691
13.250 1.2179 0.04786 0.03992 -0.0683 0.0768 0.4754
13.500 1.2226 0.05021 0.04230 -0.0679 0.0736 0.4816
13.750 1.2273 0.05263 0.04481 -0.0677 0.0706 0.4873
14.000 1.2324 0.05509 0.04736 -0.0676 0.0676 0.4935
14.250 1.2350 0.05789 0.05022 -0.0677 0.0650 0.4997
14.500 1.2401 0.06048 0.05289 -0.0678 0.0622 0.5064
14.750 1.2427 0.06345 0.05594 -0.0681 0.0597 0.5123
15.000 1.2464 0.06636 0.05895 -0.0685 0.0574 0.5192
15.250 1.2494 0.06943 0.06210 -0.0690 0.0551 0.5265
15.500 1.2502 0.07285 0.06558 -0.0697 0.0533 0.5328
15.750 1.2541 0.07596 0.06882 -0.0703 0.0511 0.5399
16.000 1.2557 0.07943 0.07238 -0.0712 0.0492 0.5474
16.500 1.2587 0.08659 0.07973 -0.0733 0.0457 0.5623
16.750 1.2595 0.09036 0.08359 -0.0745 0.0441 0.5706
17.000 1.2584 0.09445 0.08774 -0.0760 0.0428 0.5782
17.250 1.2605 0.09814 0.09157 -0.0773 0.0413 0.5864
17.500 1.2613 0.10204 0.09558 -0.0788 0.0399 0.5955
17.750 1.2602 0.10629 0.09992 -0.0806 0.0388 0.6039
18.000 1.2598 0.11048 0.10420 -0.0824 0.0377 0.6134
18.250 1.2609 0.11445 0.10830 -0.0841 0.0364 0.6237
18.500 1.2606 0.11867 0.11263 -0.0861 0.0353 0.6341
19.000 1.2580 0.12748 0.12162 -0.0905 0.0336 0.6564
19.250 1.2589 0.13150 0.12578 -0.0925 0.0326 0.6697
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