NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S814 Airfoil (s814-nr) Reynolds number: 200,000 Max Cl/Cd: 58.82 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s814-nr-200000-n5.txt Download as CSV file: xf-s814-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S814 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 -0.4422 0.12484 0.11932 -0.0332 1.0000 0.2313
-12.750 -0.4308 0.12381 0.11829 -0.0327 1.0000 0.2325
-12.250 -0.4532 0.11612 0.11052 -0.0340 1.0000 0.2419
-12.000 -0.4381 0.11559 0.10999 -0.0332 1.0000 0.2424
-11.750 -0.4243 0.11490 0.10930 -0.0325 1.0000 0.2429
-11.500 -0.4113 0.11416 0.10857 -0.0317 1.0000 0.2436
-11.250 -0.3952 0.11295 0.10735 -0.0321 0.9994 0.2443
-11.000 -0.3690 0.11113 0.10550 -0.0351 0.9972 0.2454
-10.500 -0.3683 0.10177 0.09599 -0.0433 0.9925 0.2554
-10.250 -0.3413 0.10047 0.09468 -0.0452 0.9897 0.2558
-10.000 -0.3144 0.09906 0.09325 -0.0475 0.9867 0.2563
-9.750 -0.2865 0.09768 0.09184 -0.0499 0.9841 0.2569
-9.500 -0.2584 0.09616 0.09031 -0.0526 0.9818 0.2576
-9.250 -0.2310 0.09457 0.08869 -0.0554 0.9795 0.2585
-9.000 -0.2118 0.09302 0.08714 -0.0565 0.9749 0.2594
-8.500 -0.2192 0.08340 0.07738 -0.0643 0.9674 0.2693
-8.250 -0.1987 0.08231 0.07629 -0.0647 0.9614 0.2697
-8.000 -0.1735 0.08108 0.07508 -0.0661 0.9563 0.2701
-7.750 -0.1444 0.07971 0.07370 -0.0685 0.9527 0.2706
-7.500 -0.1302 0.07879 0.07280 -0.0676 0.9421 0.2712
-7.250 -0.1154 0.07767 0.07170 -0.0671 0.9302 0.2718
-7.000 -0.1033 0.07666 0.07071 -0.0661 0.9147 0.2726
-6.750 -0.0863 0.07543 0.06948 -0.0662 0.8998 0.2735
-6.500 -0.0626 0.07390 0.06793 -0.0679 0.8861 0.2749
-6.250 -0.0349 0.07164 0.06563 -0.0715 0.8736 0.2765
-5.750 -0.0093 0.06053 0.05422 -0.0864 0.8454 0.2844
-5.500 0.0591 0.05840 0.05196 -0.0970 0.8270 0.2849
-5.000 0.1556 0.05544 0.04861 -0.1096 0.7680 0.2861
-4.500 -0.1555 0.02367 0.01590 -0.1134 0.7277 0.3115
-4.250 -0.1363 0.02180 0.01366 -0.1164 0.7106 0.3133
-4.000 -0.1105 0.02148 0.01326 -0.1167 0.6948 0.3141
-3.750 -0.0848 0.02130 0.01303 -0.1167 0.6799 0.3148
-3.500 -0.0592 0.02116 0.01282 -0.1167 0.6660 0.3155
-3.000 -0.0081 0.02080 0.01235 -0.1168 0.6412 0.3169
-2.750 0.0178 0.02057 0.01206 -0.1170 0.6306 0.3177
-2.500 0.0439 0.02035 0.01177 -0.1173 0.6203 0.3185
-2.250 0.0704 0.02011 0.01147 -0.1177 0.6108 0.3194
-2.000 0.0974 0.01988 0.01116 -0.1181 0.6020 0.3204
-1.750 0.1246 0.01962 0.01085 -0.1186 0.5935 0.3214
-1.500 0.1523 0.01939 0.01053 -0.1192 0.5856 0.3225
-1.250 0.1803 0.01914 0.01022 -0.1198 0.5780 0.3236
-1.000 0.2086 0.01890 0.00990 -0.1205 0.5704 0.3248
-0.750 0.2375 0.01869 0.00959 -0.1212 0.5640 0.3261
-0.500 0.2667 0.01846 0.00931 -0.1220 0.5574 0.3272
-0.250 0.2962 0.01829 0.00903 -0.1228 0.5517 0.3283
0.000 0.3248 0.01819 0.00892 -0.1232 0.5467 0.3293
0.250 0.3529 0.01813 0.00891 -0.1235 0.5414 0.3302
0.500 0.3813 0.01811 0.00891 -0.1237 0.5365 0.3312
0.750 0.4100 0.01812 0.00891 -0.1241 0.5323 0.3322
1.000 0.4388 0.01811 0.00893 -0.1244 0.5279 0.3333
1.250 0.4673 0.01810 0.00896 -0.1247 0.5232 0.3346
1.500 0.4962 0.01810 0.00897 -0.1251 0.5189 0.3360
1.750 0.5258 0.01813 0.00897 -0.1256 0.5153 0.3376
2.000 0.5555 0.01814 0.00898 -0.1262 0.5119 0.3394
2.250 0.5851 0.01812 0.00898 -0.1267 0.5082 0.3412
2.500 0.6149 0.01811 0.00897 -0.1273 0.5048 0.3428
2.750 0.6450 0.01812 0.00896 -0.1279 0.5016 0.3443
3.000 0.6742 0.01818 0.00906 -0.1283 0.4987 0.3456
3.250 0.7035 0.01826 0.00920 -0.1286 0.4956 0.3469
3.500 0.7315 0.01833 0.00937 -0.1287 0.4922 0.3483
3.750 0.7602 0.01841 0.00953 -0.1290 0.4892 0.3499
4.000 0.7892 0.01851 0.00969 -0.1293 0.4863 0.3516
4.250 0.8185 0.01860 0.00982 -0.1296 0.4836 0.3535
4.500 0.8486 0.01872 0.00994 -0.1301 0.4808 0.3555
4.750 0.8779 0.01884 0.01009 -0.1305 0.4779 0.3576
5.000 0.9053 0.01892 0.01024 -0.1305 0.4741 0.3596
5.250 0.9321 0.01900 0.01042 -0.1304 0.4699 0.3613
5.500 0.9593 0.01912 0.01062 -0.1303 0.4661 0.3631
5.750 0.9884 0.01929 0.01081 -0.1305 0.4624 0.3652
6.000 1.0120 0.01941 0.01107 -0.1298 0.4574 0.3675
6.250 1.0362 0.01950 0.01126 -0.1291 0.4517 0.3700
6.500 1.0623 0.01962 0.01136 -0.1287 0.4461 0.3727
6.750 1.0846 0.01973 0.01156 -0.1278 0.4396 0.3751
7.000 1.1068 0.01981 0.01170 -0.1267 0.4326 0.3772
7.250 1.1290 0.01993 0.01190 -0.1257 0.4259 0.3791
7.500 1.1482 0.02004 0.01216 -0.1241 0.4182 0.3812
7.750 1.1684 0.02019 0.01232 -0.1227 0.4115 0.3834
8.000 1.1859 0.02033 0.01261 -0.1208 0.4036 0.3858
8.250 1.2035 0.02052 0.01282 -0.1190 0.3953 0.3884
8.500 1.2206 0.02075 0.01316 -0.1172 0.3852 0.3909
8.750 1.2367 0.02103 0.01347 -0.1153 0.3741 0.3933
9.000 1.2509 0.02135 0.01388 -0.1131 0.3600 0.3956
9.250 1.2642 0.02175 0.01435 -0.1108 0.3418 0.3980
9.500 1.2729 0.02234 0.01491 -0.1080 0.3172 0.4005
9.750 1.2752 0.02325 0.01569 -0.1045 0.2885 0.4029
10.000 1.2738 0.02449 0.01680 -0.1008 0.2618 0.4054
10.250 1.2722 0.02592 0.01811 -0.0973 0.2371 0.4077
10.500 1.2698 0.02753 0.01962 -0.0942 0.2153 0.4098
10.750 1.2679 0.02926 0.02133 -0.0914 0.1953 0.4116
11.000 1.2655 0.03117 0.02322 -0.0889 0.1775 0.4135
11.250 1.2634 0.03322 0.02526 -0.0868 0.1621 0.4154
11.500 1.2609 0.03546 0.02750 -0.0850 0.1481 0.4175
11.750 1.2585 0.03788 0.02991 -0.0835 0.1358 0.4197
12.000 1.2555 0.04051 0.03255 -0.0824 0.1250 0.4220
12.250 1.2546 0.04311 0.03516 -0.0815 0.1147 0.4244
12.750 1.2509 0.04890 0.04102 -0.0805 0.0983 0.4288
13.000 1.2514 0.05172 0.04392 -0.0802 0.0912 0.4313
13.250 1.2489 0.05496 0.04720 -0.0802 0.0851 0.4337
13.500 1.2505 0.05786 0.05017 -0.0802 0.0793 0.4367
13.750 1.2490 0.06118 0.05352 -0.0804 0.0742 0.4396
14.000 1.2504 0.06425 0.05665 -0.0806 0.0697 0.4426
14.250 1.2509 0.06750 0.05997 -0.0810 0.0654 0.4452
14.500 1.2504 0.07094 0.06347 -0.0815 0.0618 0.4477
14.750 1.2533 0.07401 0.06664 -0.0820 0.0582 0.4508
15.000 1.2538 0.07744 0.07013 -0.0827 0.0550 0.4540
15.250 1.2540 0.08098 0.07373 -0.0834 0.0523 0.4574
15.500 1.2575 0.08412 0.07696 -0.0841 0.0496 0.4611
15.750 1.2591 0.08759 0.08052 -0.0849 0.0472 0.4643
16.000 1.2588 0.09135 0.08434 -0.0859 0.0451 0.4677
16.250 1.2620 0.09465 0.08774 -0.0868 0.0432 0.4718
16.500 1.2650 0.09804 0.09121 -0.0878 0.0412 0.4760
16.750 1.2667 0.10163 0.09488 -0.0890 0.0395 0.4796
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