NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S821 Airfoil (s821-nr) Reynolds number: 200,000 Max Cl/Cd: 52.79 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s821-nr-200000.txt Download as CSV file: xf-s821-nr-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.000 0.1241 0.09980 0.09497 -0.0610 0.9452 0.2525
-4.750 0.1529 0.09720 0.09239 -0.0650 0.9421 0.2563
-3.250 -0.1418 0.03053 0.02424 -0.1096 0.8539 0.2630
-3.000 -0.0985 0.02996 0.02375 -0.1122 0.8463 0.2642
-2.750 -0.0592 0.02939 0.02321 -0.1143 0.8360 0.2655
-2.500 -0.0135 0.02846 0.02224 -0.1185 0.8270 0.2672
-2.250 0.0155 0.02734 0.02103 -0.1204 0.8130 0.2690
-2.000 0.0429 0.02592 0.01945 -0.1229 0.7996 0.2713
-1.750 0.0762 0.02444 0.01771 -0.1264 0.7873 0.2743
-1.500 0.0988 0.02339 0.01642 -0.1274 0.7723 0.2766
-1.250 0.1314 0.02244 0.01534 -0.1292 0.7603 0.2786
-1.000 0.1563 0.02210 0.01504 -0.1287 0.7465 0.2801
-0.750 0.1860 0.02191 0.01484 -0.1290 0.7347 0.2817
-0.500 0.2129 0.02170 0.01462 -0.1288 0.7222 0.2834
-0.250 0.2412 0.02144 0.01431 -0.1291 0.7104 0.2855
0.000 0.2687 0.02110 0.01389 -0.1293 0.6983 0.2878
0.250 0.2974 0.02076 0.01344 -0.1298 0.6870 0.2904
0.500 0.3259 0.02044 0.01298 -0.1303 0.6756 0.2930
0.750 0.3554 0.02005 0.01252 -0.1309 0.6656 0.2956
1.000 0.3805 0.01991 0.01246 -0.1302 0.6545 0.2977
1.250 0.4111 0.01991 0.01243 -0.1305 0.6449 0.3001
1.500 0.4356 0.01981 0.01240 -0.1298 0.6340 0.3025
1.750 0.4664 0.01971 0.01221 -0.1303 0.6250 0.3056
2.000 0.4941 0.01958 0.01204 -0.1303 0.6153 0.3087
2.250 0.5236 0.01947 0.01181 -0.1306 0.6056 0.3116
2.500 0.5532 0.01927 0.01164 -0.1309 0.5972 0.3148
2.750 0.5778 0.01928 0.01178 -0.1300 0.5878 0.3176
3.000 0.6072 0.01935 0.01183 -0.1300 0.5790 0.3212
3.250 0.6342 0.01938 0.01187 -0.1297 0.5696 0.3253
3.500 0.6625 0.01934 0.01174 -0.1296 0.5598 0.3293
3.750 0.6920 0.01924 0.01163 -0.1297 0.5510 0.3331
4.000 0.7154 0.01924 0.01177 -0.1286 0.5410 0.3364
4.250 0.7446 0.01933 0.01181 -0.1284 0.5320 0.3405
4.500 0.7694 0.01936 0.01189 -0.1276 0.5224 0.3450
4.750 0.7975 0.01939 0.01182 -0.1274 0.5129 0.3495
5.000 0.8239 0.01936 0.01187 -0.1269 0.5040 0.3539
5.250 0.8467 0.01942 0.01205 -0.1256 0.4940 0.3581
5.500 0.8754 0.01958 0.01213 -0.1254 0.4849 0.3634
5.750 0.8980 0.01962 0.01222 -0.1241 0.4748 0.3686
6.000 0.9246 0.01961 0.01220 -0.1236 0.4655 0.3735
6.250 0.9460 0.01971 0.01244 -0.1221 0.4557 0.3777
6.500 0.9693 0.01981 0.01256 -0.1209 0.4456 0.3828
6.750 0.9922 0.01995 0.01269 -0.1197 0.4352 0.3885
7.000 1.0140 0.01998 0.01273 -0.1183 0.4242 0.3938
7.250 1.0333 0.02011 0.01298 -0.1164 0.4132 0.3985
7.500 1.0521 0.02029 0.01316 -0.1145 0.4015 0.4039
7.750 1.0681 0.02043 0.01335 -0.1121 0.3889 0.4097
8.000 1.0840 0.02060 0.01345 -0.1098 0.3763 0.4150
8.250 1.0965 0.02077 0.01373 -0.1069 0.3619 0.4197
8.500 1.1094 0.02111 0.01412 -0.1041 0.3464 0.4250
8.750 1.1221 0.02153 0.01452 -0.1015 0.3293 0.4310
9.000 1.1337 0.02206 0.01496 -0.0988 0.3098 0.4365
9.250 1.1425 0.02260 0.01552 -0.0959 0.2884 0.4416
9.500 1.1484 0.02341 0.01627 -0.0927 0.2662 0.4466
9.750 1.1526 0.02442 0.01715 -0.0895 0.2451 0.4521
10.000 1.1582 0.02552 0.01814 -0.0867 0.2249 0.4579
10.250 1.1630 0.02667 0.01924 -0.0841 0.2074 0.4631
10.500 1.1666 0.02797 0.02051 -0.0814 0.1925 0.4680
10.750 1.1697 0.02942 0.02189 -0.0789 0.1797 0.4736
11.000 1.1760 0.03081 0.02326 -0.0770 0.1676 0.4800
11.250 1.1824 0.03225 0.02470 -0.0752 0.1572 0.4859
11.500 1.1863 0.03388 0.02634 -0.0734 0.1484 0.4912
11.750 1.1905 0.03560 0.02807 -0.0718 0.1405 0.4972
12.000 1.1973 0.03728 0.02976 -0.0705 0.1328 0.5042
12.250 1.1998 0.03932 0.03174 -0.0693 0.1267 0.5101
12.500 1.2073 0.04101 0.03358 -0.0683 0.1200 0.5165
12.750 1.2102 0.04319 0.03573 -0.0673 0.1148 0.5232
13.000 1.2172 0.04517 0.03776 -0.0667 0.1091 0.5305
13.250 1.2206 0.04741 0.04003 -0.0660 0.1046 0.5366
13.500 1.2265 0.04955 0.04227 -0.0655 0.0996 0.5439
13.750 1.2297 0.05203 0.04470 -0.0651 0.0956 0.5517
14.000 1.2358 0.05432 0.04714 -0.0649 0.0911 0.5591
14.250 1.2390 0.05689 0.04967 -0.0646 0.0876 0.5664
14.500 1.2443 0.05944 0.05235 -0.0647 0.0835 0.5751
14.750 1.2485 0.06206 0.05499 -0.0647 0.0803 0.5827
15.000 1.2527 0.06480 0.05784 -0.0648 0.0767 0.5912
15.250 1.2570 0.06762 0.06068 -0.0652 0.0736 0.6008
15.500 1.2614 0.07039 0.06353 -0.0654 0.0707 0.6092
15.750 1.2652 0.07341 0.06665 -0.0659 0.0677 0.6194
16.000 1.2713 0.07602 0.06922 -0.0662 0.0653 0.6291
16.250 1.2738 0.07937 0.07277 -0.0670 0.0626 0.6397
16.500 1.2785 0.08237 0.07582 -0.0677 0.0603 0.6506
16.750 1.2841 0.08524 0.07873 -0.0682 0.0582 0.6633
17.000 1.2866 0.08869 0.08235 -0.0692 0.0560 0.6749
17.250 1.2925 0.09161 0.08529 -0.0700 0.0542 0.6894
17.500 1.2979 0.09456 0.08832 -0.0707 0.0524 0.7045
17.750 1.2998 0.09818 0.09213 -0.0720 0.0507 0.7200
18.000 1.3050 0.10121 0.09524 -0.0729 0.0492 0.7397
18.250 1.3167 0.10288 0.09686 -0.0727 0.0478 0.7675
18.500 1.3134 0.10694 0.10122 -0.0740 0.0466 0.7964
18.750 1.3041 0.10914 0.10373 -0.0723 0.0457 0.9126
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