NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S818 Airfoil (s818-nr) Reynolds number: 200,000 Max Cl/Cd: 58.83 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s818-nr-200000-n5.txt Download as CSV file: xf-s818-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S818 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5607 0.10009 0.09530 -0.0378 1.0000 0.2688
-12.750 -0.5397 0.10087 0.09606 -0.0368 1.0000 0.2729
-12.500 -0.5466 0.09842 0.09356 -0.0367 1.0000 0.2817
-12.250 -0.5189 0.09996 0.09507 -0.0353 1.0000 0.2839
-11.750 -0.5140 0.09750 0.09255 -0.0341 1.0000 0.2951
-11.500 -0.4754 0.09852 0.09353 -0.0347 0.9988 0.2965
-11.250 -0.4332 0.09871 0.09365 -0.0373 0.9963 0.2989
-11.000 -0.4329 0.09530 0.09015 -0.0412 0.9935 0.3075
-10.750 -0.3907 0.09551 0.09031 -0.0432 0.9911 0.3098
-10.500 -0.3518 0.09525 0.09000 -0.0452 0.9880 0.3113
-10.250 -0.3207 0.09403 0.08871 -0.0478 0.9850 0.3128
-9.750 -0.3202 0.08745 0.08198 -0.0547 0.9784 0.3228
-9.500 -0.2947 0.08580 0.08029 -0.0564 0.9743 0.3231
-9.250 -0.2660 0.08414 0.07857 -0.0589 0.9711 0.3234
-9.000 -0.2366 0.08241 0.07679 -0.0618 0.9686 0.3238
-8.750 -0.2172 0.08093 0.07528 -0.0625 0.9632 0.3241
-8.500 -0.1938 0.07941 0.07373 -0.0639 0.9582 0.3245
-8.000 -0.1485 0.07694 0.07122 -0.0657 0.9462 0.3258
-7.750 -0.1289 0.07505 0.06929 -0.0675 0.9405 0.3261
-7.500 -0.1233 0.07370 0.06794 -0.0659 0.9273 0.3264
-7.250 -0.1168 0.07238 0.06661 -0.0644 0.9115 0.3269
-4.750 -0.1363 0.02307 0.01527 -0.1087 0.7084 0.3530
-4.500 -0.1106 0.02271 0.01478 -0.1092 0.6894 0.3535
-4.250 -0.0859 0.02239 0.01434 -0.1093 0.6717 0.3540
-4.000 -0.0617 0.02211 0.01395 -0.1094 0.6554 0.3545
-3.750 -0.0377 0.02183 0.01356 -0.1094 0.6402 0.3551
-3.250 0.0105 0.02121 0.01273 -0.1096 0.6120 0.3562
-3.000 0.0352 0.02091 0.01234 -0.1097 0.5992 0.3568
-2.750 0.0601 0.02063 0.01194 -0.1100 0.5874 0.3574
-2.500 0.0855 0.02037 0.01158 -0.1102 0.5759 0.3580
-2.250 0.1116 0.02010 0.01123 -0.1106 0.5655 0.3587
-2.000 0.1379 0.01987 0.01089 -0.1110 0.5564 0.3595
-1.750 0.1649 0.01962 0.01058 -0.1115 0.5473 0.3603
-1.250 0.2200 0.01919 0.00998 -0.1126 0.5315 0.3620
-1.000 0.2478 0.01901 0.00971 -0.1132 0.5243 0.3630
-0.750 0.2764 0.01883 0.00946 -0.1139 0.5178 0.3639
-0.500 0.3051 0.01867 0.00922 -0.1146 0.5112 0.3649
-0.250 0.3339 0.01855 0.00899 -0.1154 0.5056 0.3659
0.000 0.3631 0.01841 0.00880 -0.1161 0.4997 0.3669
0.250 0.3923 0.01831 0.00863 -0.1169 0.4940 0.3677
0.500 0.4206 0.01827 0.00853 -0.1173 0.4890 0.3686
0.750 0.4486 0.01823 0.00852 -0.1176 0.4844 0.3694
1.000 0.4767 0.01822 0.00853 -0.1180 0.4799 0.3702
1.250 0.5048 0.01824 0.00857 -0.1183 0.4758 0.3710
1.500 0.5332 0.01829 0.00860 -0.1186 0.4723 0.3719
1.750 0.5620 0.01834 0.00866 -0.1191 0.4689 0.3729
2.000 0.5907 0.01837 0.00874 -0.1195 0.4653 0.3740
2.250 0.6194 0.01841 0.00880 -0.1199 0.4619 0.3751
2.500 0.6483 0.01847 0.00887 -0.1204 0.4588 0.3764
2.750 0.6777 0.01855 0.00894 -0.1210 0.4560 0.3778
3.000 0.7076 0.01866 0.00901 -0.1217 0.4533 0.3794
3.250 0.7364 0.01871 0.00911 -0.1221 0.4502 0.3810
3.500 0.7654 0.01878 0.00919 -0.1226 0.4471 0.3826
3.750 0.7947 0.01887 0.00929 -0.1232 0.4444 0.3840
4.000 0.8232 0.01895 0.00944 -0.1236 0.4420 0.3852
4.250 0.8521 0.01908 0.00962 -0.1240 0.4398 0.3864
4.500 0.8816 0.01924 0.00982 -0.1245 0.4378 0.3877
4.750 0.9111 0.01942 0.01005 -0.1250 0.4359 0.3892
5.000 0.9390 0.01956 0.01030 -0.1252 0.4337 0.3907
5.250 0.9670 0.01972 0.01056 -0.1255 0.4316 0.3923
5.500 0.9949 0.01988 0.01079 -0.1257 0.4292 0.3940
5.750 1.0228 0.02005 0.01102 -0.1260 0.4268 0.3959
6.000 1.0512 0.02023 0.01126 -0.1263 0.4247 0.3977
6.250 1.0804 0.02044 0.01149 -0.1268 0.4229 0.3996
6.500 1.1101 0.02066 0.01177 -0.1274 0.4212 0.4013
6.750 1.1404 0.02092 0.01211 -0.1281 0.4196 0.4030
7.000 1.1652 0.02114 0.01250 -0.1277 0.4174 0.4048
7.250 1.1900 0.02137 0.01288 -0.1274 0.4148 0.4069
7.500 1.2146 0.02160 0.01323 -0.1270 0.4119 0.4092
7.750 1.2390 0.02180 0.01351 -0.1265 0.4085 0.4118
8.000 1.2641 0.02193 0.01359 -0.1262 0.4030 0.4143
8.250 1.2724 0.02198 0.01379 -0.1227 0.3953 0.4163
8.500 1.2869 0.02203 0.01387 -0.1205 0.3879 0.4182
8.750 1.3035 0.02226 0.01425 -0.1187 0.3822 0.4202
9.000 1.3206 0.02251 0.01466 -0.1170 0.3768 0.4223
9.250 1.3390 0.02276 0.01496 -0.1156 0.3715 0.4246
9.500 1.3554 0.02308 0.01539 -0.1139 0.3656 0.4271
9.750 1.3705 0.02341 0.01585 -0.1120 0.3586 0.4297
10.000 1.3857 0.02376 0.01623 -0.1102 0.3521 0.4322
10.250 1.3996 0.02418 0.01683 -0.1083 0.3438 0.4346
10.500 1.4120 0.02464 0.01739 -0.1062 0.3355 0.4371
10.750 1.4239 0.02518 0.01808 -0.1042 0.3244 0.4398
11.000 1.4337 0.02583 0.01883 -0.1019 0.3105 0.4428
11.250 1.4387 0.02671 0.01973 -0.0992 0.2910 0.4458
11.500 1.4356 0.02807 0.02099 -0.0958 0.2632 0.4484
11.750 1.4236 0.03015 0.02293 -0.0919 0.2362 0.4504
12.000 1.4098 0.03272 0.02543 -0.0885 0.2136 0.4521
12.250 1.3965 0.03560 0.02828 -0.0859 0.1931 0.4538
12.500 1.3831 0.03883 0.03151 -0.0838 0.1754 0.4557
12.750 1.3702 0.04236 0.03504 -0.0824 0.1604 0.4576
13.000 1.3579 0.04614 0.03884 -0.0814 0.1475 0.4596
13.250 1.3451 0.05024 0.04297 -0.0810 0.1360 0.4617
13.500 1.3340 0.05439 0.04715 -0.0809 0.1257 0.4639
13.750 1.3248 0.05854 0.05134 -0.0810 0.1169 0.4662
14.000 1.3139 0.06301 0.05587 -0.0814 0.1092 0.4681
14.250 1.3074 0.06711 0.06005 -0.0820 0.1017 0.4703
14.500 1.2988 0.07158 0.06457 -0.0827 0.0955 0.4726
14.750 1.2947 0.07557 0.06864 -0.0835 0.0892 0.4756
15.250 1.2865 0.08375 0.07694 -0.0853 0.0789 0.4820
15.500 1.2829 0.08789 0.08113 -0.0863 0.0741 0.4851
15.750 1.2812 0.09183 0.08516 -0.0874 0.0700 0.4883
16.000 1.2814 0.09553 0.08893 -0.0885 0.0658 0.4922
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