NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 500,000 Max Cl/Cd: 98.09 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s804-nr-500000.txt Download as CSV file: xf-s804-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S804 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6300 0.06933 0.06603 -0.0750 1.0000 0.0215
-13.750 -0.6755 0.06002 0.05642 -0.0811 1.0000 0.0213
-13.500 -0.6987 0.05468 0.05090 -0.0838 1.0000 0.0213
-13.250 -0.7128 0.05083 0.04694 -0.0851 1.0000 0.0214
-13.000 -0.7279 0.04716 0.04314 -0.0861 1.0000 0.0214
-12.750 -0.7332 0.04480 0.04073 -0.0860 1.0000 0.0215
-12.500 -0.7423 0.04233 0.03818 -0.0856 1.0000 0.0216
-12.250 -0.7562 0.03978 0.03552 -0.0846 1.0000 0.0216
-12.000 -0.7679 0.03802 0.03371 -0.0827 1.0000 0.0217
-11.750 -0.7523 0.03618 0.03182 -0.0854 0.9974 0.0221
-11.500 -0.7255 0.03393 0.02945 -0.0906 0.9925 0.0225
-11.250 -0.6997 0.03145 0.02680 -0.0954 0.9857 0.0228
-11.000 -0.6675 0.02907 0.02422 -0.1005 0.9804 0.0233
-10.750 -0.6395 0.02718 0.02213 -0.1036 0.9721 0.0238
-10.500 -0.6140 0.02571 0.02047 -0.1054 0.9613 0.0242
-10.250 -0.5901 0.02400 0.01869 -0.1062 0.9488 0.0247
-10.000 -0.5605 0.02290 0.01760 -0.1076 0.9367 0.0254
-9.750 -0.5200 0.02180 0.01644 -0.1111 0.9267 0.0262
-9.500 -0.4681 0.02061 0.01513 -0.1168 0.9155 0.0272
-9.250 -0.4087 0.01927 0.01359 -0.1241 0.8976 0.0284
-9.000 -0.3648 0.01824 0.01247 -0.1280 0.8606 0.0293
-8.750 -0.3361 0.01771 0.01175 -0.1288 0.8259 0.0302
-8.500 -0.3134 0.01728 0.01113 -0.1283 0.7988 0.0311
-8.250 -0.2911 0.01689 0.01057 -0.1277 0.7741 0.0320
-8.000 -0.2706 0.01622 0.00981 -0.1269 0.7527 0.0329
-7.750 -0.2480 0.01578 0.00930 -0.1265 0.7339 0.0340
-7.500 -0.2241 0.01544 0.00885 -0.1261 0.7163 0.0354
-7.250 -0.1995 0.01516 0.00842 -0.1256 0.6994 0.0365
-7.000 -0.1760 0.01453 0.00775 -0.1255 0.6831 0.0380
-6.750 -0.1505 0.01417 0.00732 -0.1254 0.6681 0.0395
-6.500 -0.1244 0.01389 0.00692 -0.1252 0.6541 0.0411
-6.250 -0.0984 0.01344 0.00642 -0.1253 0.6406 0.0432
-6.000 -0.0712 0.01316 0.00608 -0.1253 0.6282 0.0456
-5.750 -0.0443 0.01283 0.00567 -0.1254 0.6161 0.0485
-5.500 -0.0163 0.01256 0.00535 -0.1255 0.6043 0.0520
-5.250 0.0115 0.01226 0.00501 -0.1257 0.5934 0.0577
-5.000 0.0398 0.01190 0.00466 -0.1261 0.5823 0.0687
-4.750 0.0683 0.01146 0.00432 -0.1266 0.5719 0.0985
-4.500 0.0971 0.01105 0.00404 -0.1271 0.5613 0.1415
-4.250 0.1261 0.01067 0.00379 -0.1277 0.5515 0.1901
-4.000 0.1554 0.01029 0.00357 -0.1284 0.5417 0.2456
-3.750 0.1848 0.00992 0.00338 -0.1291 0.5330 0.3127
-3.500 0.2145 0.00969 0.00333 -0.1296 0.5242 0.3789
-3.250 0.2431 0.00973 0.00334 -0.1296 0.5157 0.4144
-3.000 0.2724 0.00975 0.00336 -0.1298 0.5081 0.4354
-2.750 0.3011 0.00985 0.00338 -0.1297 0.5003 0.4522
-2.500 0.3298 0.00995 0.00346 -0.1297 0.4933 0.4684
-2.250 0.3587 0.01003 0.00352 -0.1297 0.4863 0.4809
-2.000 0.3872 0.01020 0.00357 -0.1296 0.4794 0.4911
-1.750 0.4157 0.01026 0.00363 -0.1296 0.4732 0.4998
-1.500 0.4444 0.01037 0.00369 -0.1296 0.4668 0.5081
-1.250 0.4728 0.01050 0.00372 -0.1295 0.4607 0.5148
-1.000 0.5010 0.01058 0.00379 -0.1294 0.4554 0.5212
-0.750 0.5298 0.01065 0.00385 -0.1294 0.4504 0.5274
-0.500 0.5584 0.01078 0.00390 -0.1294 0.4453 0.5331
-0.250 0.5863 0.01088 0.00394 -0.1293 0.4404 0.5387
0.000 0.6146 0.01098 0.00404 -0.1293 0.4362 0.5441
0.250 0.6433 0.01105 0.00411 -0.1293 0.4322 0.5495
0.500 0.6719 0.01116 0.00417 -0.1293 0.4281 0.5543
0.750 0.6999 0.01125 0.00421 -0.1293 0.4241 0.5587
1.000 0.7275 0.01143 0.00434 -0.1292 0.4196 0.5629
1.250 0.7561 0.01147 0.00441 -0.1292 0.4167 0.5670
1.500 0.7846 0.01155 0.00448 -0.1293 0.4134 0.5712
1.750 0.8129 0.01166 0.00456 -0.1293 0.4102 0.5754
2.000 0.8410 0.01176 0.00464 -0.1293 0.4071 0.5793
2.250 0.8686 0.01190 0.00476 -0.1292 0.4040 0.5834
2.500 0.8965 0.01211 0.00495 -0.1292 0.4008 0.5876
2.750 0.9247 0.01220 0.00506 -0.1292 0.3987 0.5925
3.000 0.9528 0.01231 0.00518 -0.1292 0.3964 0.5972
3.250 0.9807 0.01240 0.00530 -0.1292 0.3939 0.6018
3.500 1.0084 0.01251 0.00544 -0.1291 0.3915 0.6066
3.750 1.0359 0.01266 0.00558 -0.1290 0.3889 0.6118
4.000 1.0635 0.01285 0.00574 -0.1290 0.3864 0.6172
4.250 1.0912 0.01312 0.00599 -0.1290 0.3836 0.6229
4.500 1.1187 0.01327 0.00620 -0.1290 0.3819 0.6290
4.750 1.1462 0.01340 0.00638 -0.1289 0.3803 0.6356
5.000 1.1736 0.01355 0.00656 -0.1288 0.3784 0.6419
5.250 1.2008 0.01368 0.00676 -0.1287 0.3765 0.6486
5.500 1.2279 0.01384 0.00696 -0.1286 0.3744 0.6561
5.750 1.2548 0.01400 0.00714 -0.1285 0.3723 0.6636
6.000 1.2815 0.01418 0.00736 -0.1283 0.3704 0.6719
6.250 1.3086 0.01443 0.00761 -0.1283 0.3685 0.6812
6.500 1.3360 0.01476 0.00796 -0.1283 0.3660 0.6903
6.750 1.3628 0.01499 0.00825 -0.1282 0.3642 0.7005
7.000 1.3883 0.01511 0.00849 -0.1278 0.3626 0.7106
7.250 1.4140 0.01527 0.00872 -0.1275 0.3606 0.7220
7.500 1.4394 0.01542 0.00896 -0.1271 0.3584 0.7340
7.750 1.4645 0.01557 0.00918 -0.1267 0.3560 0.7469
8.000 1.4893 0.01572 0.00938 -0.1262 0.3535 0.7617
8.250 1.5139 0.01594 0.00963 -0.1258 0.3507 0.7780
8.500 1.5397 0.01632 0.01003 -0.1256 0.3474 0.7955
8.750 1.5616 0.01639 0.01026 -0.1246 0.3455 0.8152
9.000 1.5823 0.01647 0.01049 -0.1233 0.3429 0.8389
9.250 1.6019 0.01655 0.01069 -0.1218 0.3399 0.8752
9.500 1.6191 0.01656 0.01082 -0.1198 0.3371 0.9219
9.750 1.6410 0.01673 0.01101 -0.1189 0.3342 1.0000
10.000 1.6663 0.01718 0.01141 -0.1188 0.3307 1.0000
10.250 1.6859 0.01734 0.01167 -0.1176 0.3284 1.0000
10.500 1.7044 0.01753 0.01194 -0.1161 0.3255 1.0000
10.750 1.7222 0.01775 0.01221 -0.1145 0.3223 1.0000
11.000 1.7394 0.01800 0.01249 -0.1129 0.3191 1.0000
11.250 1.7570 0.01838 0.01284 -0.1114 0.3155 1.0000
11.500 1.7732 0.01872 0.01326 -0.1097 0.3122 1.0000
11.750 1.7883 0.01902 0.01366 -0.1079 0.3086 1.0000
12.000 1.8033 0.01937 0.01407 -0.1061 0.3047 1.0000
12.250 1.8166 0.01983 0.01454 -0.1042 0.3006 1.0000
12.500 1.8298 0.02037 0.01512 -0.1024 0.2964 1.0000
12.750 1.8438 0.02083 0.01570 -0.1007 0.2916 1.0000
13.000 1.8549 0.02147 0.01637 -0.0988 0.2863 1.0000
13.250 1.8641 0.02226 0.01719 -0.0968 0.2810 1.0000
13.500 1.8756 0.02300 0.01802 -0.0952 0.2741 1.0000
13.750 1.8799 0.02416 0.01919 -0.0930 0.2672 1.0000
14.000 1.8882 0.02523 0.02033 -0.0914 0.2584 1.0000
14.250 1.8897 0.02681 0.02193 -0.0894 0.2489 1.0000
14.500 1.8857 0.02892 0.02403 -0.0873 0.2382 1.0000
14.750 1.8797 0.03139 0.02652 -0.0856 0.2259 1.0000
15.000 1.8693 0.03446 0.02958 -0.0840 0.2141 1.0000
15.250 1.8550 0.03812 0.03325 -0.0826 0.2031 1.0000
15.500 1.8371 0.04240 0.03755 -0.0817 0.1933 1.0000
15.750 1.8163 0.04726 0.04244 -0.0812 0.1839 1.0000
16.000 1.7987 0.05206 0.04729 -0.0811 0.1751 1.0000
16.250 1.7755 0.05775 0.05302 -0.0814 0.1676 1.0000
16.500 1.7552 0.06337 0.05869 -0.0820 0.1597 1.0000
16.750 1.7345 0.06923 0.06461 -0.0829 0.1530 1.0000
17.000 1.7132 0.07541 0.07084 -0.0841 0.1461 1.0000
17.250 1.6950 0.08133 0.07681 -0.0854 0.1399 1.0000
17.500 1.6758 0.08754 0.08307 -0.0870 0.1336 1.0000
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