NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S815 Airfoil (s815-nr) Reynolds number: 500,000 Max Cl/Cd: 79.52 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s815-nr-500000.txt Download as CSV file: xf-s815-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S815 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.0076 0.09940 0.09570 -0.0705 0.9691 0.2691
-8.000 0.0224 0.09753 0.09383 -0.0739 0.9672 0.2707
-6.250 -0.4329 0.02170 0.01674 -0.1015 0.8640 0.3028
-6.000 -0.3733 0.02043 0.01533 -0.1102 0.8511 0.3037
-5.750 -0.3169 0.01947 0.01420 -0.1178 0.8307 0.3045
-5.500 -0.2828 0.01878 0.01332 -0.1208 0.8028 0.3052
-5.250 -0.2575 0.01828 0.01262 -0.1218 0.7759 0.3058
-5.000 -0.2364 0.01787 0.01203 -0.1218 0.7512 0.3063
-4.750 -0.2157 0.01752 0.01153 -0.1215 0.7284 0.3068
-4.500 -0.1944 0.01724 0.01110 -0.1211 0.7076 0.3073
-4.250 -0.1722 0.01702 0.01075 -0.1208 0.6888 0.3078
-4.000 -0.1491 0.01685 0.01046 -0.1205 0.6718 0.3083
-3.500 -0.1011 0.01645 0.00985 -0.1203 0.6413 0.3090
-3.250 -0.0777 0.01575 0.00904 -0.1205 0.6284 0.3101
-3.000 -0.0532 0.01543 0.00863 -0.1204 0.6159 0.3110
-2.750 -0.0273 0.01519 0.00836 -0.1205 0.6044 0.3118
-2.500 -0.0013 0.01505 0.00816 -0.1205 0.5939 0.3125
-2.250 0.0254 0.01491 0.00800 -0.1206 0.5839 0.3131
-2.000 0.0522 0.01484 0.00787 -0.1207 0.5750 0.3138
-1.750 0.0798 0.01472 0.00775 -0.1209 0.5665 0.3145
-1.500 0.1071 0.01467 0.00763 -0.1210 0.5583 0.3152
-1.250 0.1353 0.01457 0.00753 -0.1214 0.5512 0.3160
-1.000 0.1634 0.01449 0.00742 -0.1216 0.5440 0.3168
-0.750 0.1919 0.01446 0.00732 -0.1220 0.5375 0.3176
-0.500 0.2209 0.01436 0.00723 -0.1225 0.5322 0.3185
-0.250 0.2500 0.01428 0.00713 -0.1229 0.5268 0.3193
0.000 0.2792 0.01424 0.00705 -0.1234 0.5217 0.3202
0.250 0.3095 0.01425 0.00699 -0.1240 0.5168 0.3211
0.500 0.3389 0.01416 0.00692 -0.1245 0.5130 0.3220
0.750 0.3687 0.01411 0.00686 -0.1250 0.5089 0.3228
1.000 0.3985 0.01409 0.00682 -0.1255 0.5050 0.3235
1.250 0.4289 0.01412 0.00680 -0.1262 0.5012 0.3242
1.500 0.4604 0.01420 0.00683 -0.1270 0.4973 0.3247
1.750 0.4898 0.01395 0.00664 -0.1275 0.4943 0.3264
2.000 0.5195 0.01386 0.00660 -0.1280 0.4912 0.3279
2.250 0.5493 0.01385 0.00662 -0.1284 0.4882 0.3291
2.500 0.5794 0.01388 0.00668 -0.1289 0.4854 0.3305
2.750 0.6100 0.01396 0.00676 -0.1295 0.4826 0.3319
3.000 0.6425 0.01410 0.00689 -0.1304 0.4796 0.3334
3.250 0.6736 0.01418 0.00700 -0.1311 0.4773 0.3349
3.500 0.7028 0.01420 0.00707 -0.1314 0.4751 0.3363
3.750 0.7323 0.01423 0.00713 -0.1317 0.4726 0.3377
4.000 0.7622 0.01428 0.00721 -0.1320 0.4701 0.3391
4.250 0.7920 0.01435 0.00728 -0.1324 0.4675 0.3402
4.500 0.8212 0.01442 0.00735 -0.1326 0.4644 0.3412
4.750 0.8535 0.01446 0.00740 -0.1336 0.4607 0.3438
5.000 0.8835 0.01453 0.00755 -0.1340 0.4580 0.3458
5.250 0.9098 0.01454 0.00764 -0.1337 0.4550 0.3476
5.500 0.9360 0.01457 0.00773 -0.1333 0.4512 0.3495
5.750 0.9621 0.01461 0.00780 -0.1328 0.4472 0.3515
6.000 0.9898 0.01473 0.00790 -0.1328 0.4427 0.3536
6.250 1.0171 0.01485 0.00805 -0.1326 0.4384 0.3556
6.500 1.0381 0.01484 0.00810 -0.1312 0.4342 0.3572
6.750 1.0602 0.01481 0.00811 -0.1300 0.4294 0.3595
7.000 1.0846 0.01485 0.00820 -0.1293 0.4247 0.3624
7.250 1.1105 0.01500 0.00839 -0.1289 0.4200 0.3650
7.500 1.1314 0.01504 0.00853 -0.1275 0.4155 0.3676
7.750 1.1534 0.01514 0.00868 -0.1263 0.4104 0.3703
8.000 1.1755 0.01533 0.00885 -0.1252 0.4046 0.3730
8.250 1.1972 0.01547 0.00905 -0.1240 0.3988 0.3751
8.500 1.2195 0.01552 0.00919 -0.1230 0.3919 0.3787
8.750 1.2396 0.01574 0.00942 -0.1216 0.3849 0.3817
9.000 1.2617 0.01587 0.00966 -0.1205 0.3772 0.3847
9.250 1.2802 0.01612 0.00991 -0.1189 0.3676 0.3877
9.500 1.3001 0.01635 0.01019 -0.1175 0.3548 0.3906
9.750 1.3162 0.01672 0.01052 -0.1156 0.3380 0.3929
10.000 1.3277 0.01727 0.01100 -0.1131 0.3136 0.3962
10.250 1.3316 0.01824 0.01182 -0.1097 0.2807 0.3990
10.500 1.3335 0.01943 0.01287 -0.1063 0.2512 0.4014
10.750 1.3348 0.02073 0.01405 -0.1029 0.2262 0.4039
11.000 1.3366 0.02207 0.01530 -0.0998 0.2032 0.4065
11.250 1.3372 0.02355 0.01669 -0.0968 0.1832 0.4089
11.500 1.3375 0.02514 0.01819 -0.0940 0.1659 0.4109
11.750 1.3379 0.02684 0.01985 -0.0916 0.1503 0.4135
12.000 1.3388 0.02863 0.02163 -0.0895 0.1369 0.4165
12.250 1.3395 0.03056 0.02357 -0.0876 0.1253 0.4192
12.500 1.3391 0.03270 0.02571 -0.0860 0.1150 0.4220
12.750 1.3375 0.03509 0.02810 -0.0845 0.1060 0.4248
13.000 1.3362 0.03759 0.03060 -0.0833 0.0975 0.4274
13.250 1.3361 0.04014 0.03316 -0.0824 0.0904 0.4297
13.500 1.3337 0.04306 0.03611 -0.0818 0.0839 0.4327
13.750 1.3331 0.04591 0.03902 -0.0814 0.0780 0.4358
14.000 1.3318 0.04895 0.04210 -0.0811 0.0729 0.4386
14.250 1.3296 0.05216 0.04535 -0.0809 0.0681 0.4414
14.500 1.3286 0.05532 0.04856 -0.0809 0.0640 0.4443
14.750 1.3263 0.05871 0.05197 -0.0810 0.0602 0.4469
15.000 1.3251 0.06207 0.05537 -0.0812 0.0568 0.4492
15.250 1.3244 0.06549 0.05887 -0.0817 0.0534 0.4528
15.500 1.3230 0.06903 0.06247 -0.0822 0.0505 0.4560
15.750 1.3237 0.07238 0.06588 -0.0827 0.0477 0.4594
16.000 1.3198 0.07635 0.06989 -0.0834 0.0453 0.4624
16.250 1.3227 0.07950 0.07310 -0.0839 0.0429 0.4659
16.500 1.3216 0.08322 0.07685 -0.0847 0.0408 0.4688
16.750 1.3217 0.08692 0.08064 -0.0857 0.0388 0.4729
17.000 1.3238 0.09035 0.08415 -0.0865 0.0370 0.4770
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