NREL's S822 Airfoil (s822-nr) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S822 Airfoil (s822-nr) Reynolds number: 50,000 Max Cl/Cd: 27.66 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s822-nr-50000.txt Download as CSV file: xf-s822-nr-50000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S822 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3263 0.12745 0.12094 -0.0270 1.0000 0.3459
-11.000 -0.7535 0.07613 0.06968 -0.0622 1.0000 0.1349
-10.750 -0.7839 0.07366 0.06720 -0.0579 1.0000 0.1342
-10.500 -0.8154 0.07132 0.06483 -0.0529 1.0000 0.1335
-10.250 -0.8458 0.06853 0.06193 -0.0482 1.0000 0.1331
-10.000 -0.8737 0.06543 0.05866 -0.0437 1.0000 0.1330
-9.750 -0.8987 0.06221 0.05517 -0.0391 1.0000 0.1335
-9.500 -0.9198 0.05885 0.05144 -0.0348 1.0000 0.1344
-9.250 -0.9208 0.05588 0.04837 -0.0320 1.0000 0.1382
-9.000 -0.9185 0.05371 0.04608 -0.0292 1.0000 0.1443
-8.750 -0.9301 0.05056 0.04233 -0.0253 1.0000 0.1489
-8.500 -0.9178 0.04862 0.04051 -0.0235 1.0000 0.1578
-8.250 -0.9178 0.04572 0.03709 -0.0205 1.0000 0.1650
-8.000 -0.9079 0.04398 0.03522 -0.0183 1.0000 0.1772
-7.750 -0.8956 0.04216 0.03336 -0.0164 1.0000 0.1901
-7.500 -0.8844 0.04046 0.03149 -0.0143 1.0000 0.2057
-7.250 -0.8723 0.03881 0.02968 -0.0123 1.0000 0.2230
-7.000 -0.8570 0.03763 0.02868 -0.0105 1.0000 0.2431
-6.750 -0.8439 0.03626 0.02718 -0.0086 1.0000 0.2660
-6.500 -0.8284 0.03527 0.02637 -0.0068 1.0000 0.2908
-6.250 -0.8136 0.03427 0.02544 -0.0048 1.0000 0.3184
-6.000 -0.7984 0.03340 0.02466 -0.0029 1.0000 0.3482
-5.750 -0.7830 0.03265 0.02398 -0.0009 1.0000 0.3801
-5.500 -0.7676 0.03198 0.02338 0.0012 1.0000 0.4147
-5.250 -0.7519 0.03152 0.02307 0.0035 1.0000 0.4497
-5.000 -0.7360 0.03128 0.02301 0.0061 1.0000 0.4848
-4.750 -0.7208 0.03113 0.02292 0.0087 1.0000 0.5221
-4.500 -0.7055 0.03139 0.02333 0.0119 1.0000 0.5556
-4.250 -0.6907 0.03181 0.02380 0.0154 1.0000 0.5885
-4.000 -0.6765 0.03229 0.02430 0.0190 1.0000 0.6206
-3.750 -0.6630 0.03283 0.02484 0.0229 1.0000 0.6514
-3.500 -0.6498 0.03340 0.02539 0.0269 1.0000 0.6806
-3.250 -0.6371 0.03401 0.02595 0.0311 1.0000 0.7089
-3.000 -0.6243 0.03458 0.02643 0.0352 1.0000 0.7370
-2.750 -0.6115 0.03510 0.02686 0.0391 1.0000 0.7652
-2.500 -0.5981 0.03556 0.02722 0.0428 1.0000 0.7936
-2.250 -0.5786 0.03620 0.02775 0.0456 1.0000 0.8205
-2.000 -0.5520 0.03687 0.02825 0.0469 1.0000 0.8483
-1.750 -0.5113 0.03774 0.02893 0.0451 1.0000 0.8759
-1.500 -0.4519 0.03889 0.02983 0.0392 1.0000 0.9024
-1.250 -0.3755 0.04018 0.03084 0.0294 1.0000 0.9276
-1.000 -0.2888 0.04133 0.03172 0.0169 1.0000 0.9497
-0.750 -0.2124 0.04212 0.03230 0.0056 1.0000 0.9726
-0.500 -0.1312 0.04290 0.03288 -0.0074 1.0000 0.9952
-0.250 -0.1140 0.04267 0.03255 -0.0087 1.0000 1.0000
0.000 -0.1155 0.04213 0.03195 -0.0064 1.0000 1.0000
0.250 -0.1168 0.04162 0.03137 -0.0040 1.0000 1.0000
0.500 -0.1181 0.04113 0.03084 -0.0015 1.0000 1.0000
0.750 -0.1194 0.04066 0.03032 0.0010 1.0000 1.0000
1.000 -0.1207 0.04020 0.02981 0.0037 1.0000 1.0000
1.250 -0.1219 0.03975 0.02932 0.0064 1.0000 1.0000
1.500 -0.1230 0.03931 0.02884 0.0091 1.0000 1.0000
1.750 -0.1237 0.03890 0.02839 0.0118 1.0000 1.0000
2.000 -0.1234 0.03855 0.02800 0.0144 1.0000 1.0000
2.250 -0.1216 0.03829 0.02770 0.0167 1.0000 1.0000
2.500 -0.1174 0.03819 0.02755 0.0187 1.0000 1.0000
2.750 -0.1095 0.03832 0.02763 0.0200 1.0000 1.0000
3.000 -0.0986 0.03866 0.02794 0.0207 1.0000 1.0000
3.250 -0.0856 0.03919 0.02843 0.0211 1.0000 1.0000
3.500 -0.0715 0.03986 0.02906 0.0212 1.0000 1.0000
3.750 -0.0566 0.04064 0.02982 0.0211 1.0000 1.0000
4.000 -0.0414 0.04153 0.03070 0.0209 1.0000 1.0000
4.250 -0.0260 0.04250 0.03167 0.0206 1.0000 1.0000
4.500 -0.0107 0.04357 0.03274 0.0203 1.0000 1.0000
4.750 0.0223 0.04603 0.03523 0.0165 0.9923 1.0000
5.250 0.1074 0.05232 0.04163 0.0054 0.9554 1.0000
5.500 0.1371 0.05393 0.04334 0.0024 0.9309 1.0000
5.750 0.1745 0.05622 0.04572 -0.0015 0.9022 1.0000
6.000 0.2961 0.05721 0.04691 -0.0119 0.7890 1.0000
6.250 0.3450 0.05820 0.04802 -0.0150 0.7636 1.0000
6.500 0.3639 0.05880 0.04872 -0.0146 0.7401 1.0000
6.750 0.4060 0.05942 0.04949 -0.0165 0.7179 1.0000
7.000 0.4337 0.05990 0.05011 -0.0168 0.6951 1.0000
7.250 0.4719 0.06013 0.05052 -0.0178 0.6735 1.0000
7.500 0.5043 0.06021 0.05077 -0.0180 0.6508 1.0000
7.750 0.5413 0.05988 0.05063 -0.0181 0.6284 1.0000
8.000 0.5824 0.05894 0.04993 -0.0181 0.6055 1.0000
8.250 0.6157 0.05806 0.04926 -0.0172 0.5814 1.0000
8.500 0.6846 0.05387 0.04544 -0.0170 0.5595 1.0000
8.750 0.7292 0.05059 0.04246 -0.0150 0.5334 1.0000
9.000 0.8629 0.03774 0.03014 -0.0143 0.4983 1.0000
9.250 0.9283 0.03358 0.02564 -0.0130 0.4235 1.0000
9.500 0.9486 0.03429 0.02583 -0.0105 0.3609 1.0000
9.750 0.9657 0.03578 0.02688 -0.0084 0.3102 1.0000
10.000 0.9834 0.03754 0.02832 -0.0069 0.2698 1.0000
10.250 1.0054 0.03944 0.02997 -0.0061 0.2358 1.0000
10.500 1.0291 0.04161 0.03206 -0.0056 0.2085 1.0000
10.750 1.0568 0.04397 0.03430 -0.0058 0.1854 1.0000
11.000 1.0762 0.04654 0.03699 -0.0050 0.1691 1.0000
11.250 1.0936 0.04916 0.03969 -0.0041 0.1557 1.0000
11.500 1.1182 0.05228 0.04286 -0.0042 0.1440 1.0000
11.750 1.1092 0.05481 0.04581 -0.0002 0.1390 1.0000
12.000 1.1322 0.05827 0.04927 -0.0004 0.1303 1.0000
12.250 1.1156 0.06124 0.05266 0.0038 0.1285 1.0000
12.500 1.0973 0.06451 0.05629 0.0075 0.1269 1.0000
12.750 1.0771 0.06803 0.06012 0.0107 0.1256 1.0000
13.000 1.0537 0.07196 0.06433 0.0132 0.1248 1.0000
13.250 1.0252 0.07658 0.06922 0.0151 0.1252 1.0000
13.500 0.9921 0.08201 0.07488 0.0160 0.1263 1.0000
13.750 0.9587 0.08827 0.08133 0.0157 0.1280 1.0000
14.000 0.9256 0.09536 0.08855 0.0141 0.1295 1.0000
14.250 0.8966 0.10316 0.09642 0.0116 0.1307 1.0000
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