NREL's S804 Airfoil (s804-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S804 Airfoil (s804-nr) Reynolds number: 500,000 Max Cl/Cd: 98.6 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s804-nr-500000-n5.txt Download as CSV file: xf-s804-nr-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6637 0.10448 0.10104 -0.0543 1.0000 0.0147
-16.500 -0.6952 0.09486 0.09125 -0.0597 1.0000 0.0147
-16.250 -0.7138 0.08795 0.08422 -0.0634 1.0000 0.0148
-16.000 -0.7312 0.08152 0.07768 -0.0669 1.0000 0.0148
-15.750 -0.7442 0.07594 0.07201 -0.0698 1.0000 0.0149
-15.500 -0.7562 0.07071 0.06668 -0.0726 1.0000 0.0149
-15.250 -0.7664 0.06593 0.06181 -0.0750 1.0000 0.0150
-15.000 -0.7739 0.06174 0.05755 -0.0771 1.0000 0.0151
-14.750 -0.7810 0.05780 0.05353 -0.0789 1.0000 0.0152
-14.500 -0.7879 0.05413 0.04978 -0.0804 1.0000 0.0152
-14.250 -0.7922 0.05100 0.04659 -0.0815 1.0000 0.0154
-14.000 -0.7975 0.04800 0.04351 -0.0822 1.0000 0.0154
-13.750 -0.8011 0.04532 0.04078 -0.0827 1.0000 0.0155
-13.500 -0.8049 0.04279 0.03819 -0.0829 1.0000 0.0156
-13.250 -0.8080 0.04050 0.03584 -0.0827 1.0000 0.0158
-13.000 -0.8038 0.03814 0.03341 -0.0840 0.9992 0.0159
-12.750 -0.7828 0.03579 0.03098 -0.0879 0.9963 0.0162
-12.500 -0.7612 0.03358 0.02869 -0.0917 0.9924 0.0164
-12.250 -0.7437 0.03150 0.02652 -0.0945 0.9871 0.0167
-12.000 -0.7218 0.02962 0.02455 -0.0976 0.9812 0.0170
-11.750 -0.7180 0.02808 0.02294 -0.0968 0.9649 0.0172
-11.500 -0.7055 0.02659 0.02136 -0.0973 0.9443 0.0175
-11.250 -0.6723 0.02475 0.01944 -0.1020 0.9274 0.0179
-11.000 -0.6092 0.02298 0.01759 -0.1117 0.9129 0.0185
-10.750 -0.5361 0.02156 0.01601 -0.1227 0.8834 0.0193
-10.500 -0.4988 0.02059 0.01473 -0.1268 0.8295 0.0198
-10.250 -0.4835 0.01984 0.01376 -0.1266 0.7961 0.0202
-10.000 -0.4671 0.01920 0.01293 -0.1261 0.7684 0.0206
-9.750 -0.4499 0.01862 0.01220 -0.1254 0.7445 0.0210
-9.500 -0.4316 0.01801 0.01148 -0.1249 0.7244 0.0214
-9.250 -0.4109 0.01755 0.01091 -0.1244 0.7053 0.0219
-9.000 -0.3890 0.01711 0.01037 -0.1240 0.6886 0.0224
-8.750 -0.3663 0.01670 0.00985 -0.1237 0.6726 0.0231
-8.500 -0.3429 0.01633 0.00935 -0.1234 0.6574 0.0238
-8.250 -0.3185 0.01596 0.00888 -0.1232 0.6428 0.0245
-8.000 -0.2941 0.01553 0.00839 -0.1231 0.6296 0.0253
-7.500 -0.2427 0.01488 0.00758 -0.1231 0.6061 0.0270
-7.250 -0.2166 0.01460 0.00720 -0.1230 0.5948 0.0279
-7.000 -0.1900 0.01424 0.00678 -0.1231 0.5830 0.0288
-6.750 -0.1633 0.01396 0.00644 -0.1231 0.5722 0.0299
-6.500 -0.1359 0.01371 0.00612 -0.1232 0.5614 0.0313
-6.250 -0.1085 0.01347 0.00581 -0.1233 0.5521 0.0327
-6.000 -0.0806 0.01321 0.00551 -0.1235 0.5427 0.0344
-5.750 -0.0528 0.01302 0.00524 -0.1236 0.5342 0.0362
-5.500 -0.0244 0.01278 0.00497 -0.1238 0.5257 0.0386
-5.250 0.0036 0.01260 0.00474 -0.1240 0.5172 0.0420
-5.000 0.0323 0.01239 0.00451 -0.1242 0.5097 0.0471
-4.750 0.0608 0.01218 0.00430 -0.1245 0.5012 0.0554
-4.500 0.0894 0.01197 0.00410 -0.1247 0.4936 0.0686
-4.250 0.1184 0.01174 0.00390 -0.1251 0.4855 0.0865
-4.000 0.1471 0.01155 0.00373 -0.1254 0.4780 0.1076
-3.750 0.1764 0.01133 0.00357 -0.1259 0.4718 0.1324
-3.500 0.2058 0.01109 0.00342 -0.1263 0.4652 0.1647
-3.250 0.2350 0.01087 0.00327 -0.1268 0.4589 0.2033
-3.000 0.2647 0.01063 0.00314 -0.1274 0.4535 0.2461
-2.750 0.2947 0.01034 0.00301 -0.1280 0.4477 0.3029
-2.500 0.3244 0.01011 0.00298 -0.1286 0.4420 0.3770
-2.250 0.3535 0.01010 0.00301 -0.1288 0.4371 0.4134
-2.000 0.3827 0.01012 0.00304 -0.1289 0.4323 0.4329
-1.750 0.4116 0.01017 0.00307 -0.1290 0.4271 0.4474
-1.500 0.4402 0.01025 0.00310 -0.1290 0.4219 0.4583
-1.250 0.4689 0.01032 0.00314 -0.1290 0.4175 0.4677
-1.000 0.4978 0.01037 0.00316 -0.1291 0.4132 0.4748
-0.750 0.5265 0.01044 0.00321 -0.1291 0.4090 0.4820
-0.500 0.5549 0.01053 0.00325 -0.1291 0.4050 0.4889
0.000 0.6119 0.01069 0.00336 -0.1291 0.3983 0.5008
0.250 0.6406 0.01076 0.00342 -0.1291 0.3950 0.5067
0.500 0.6690 0.01085 0.00347 -0.1291 0.3917 0.5116
0.750 0.6972 0.01094 0.00353 -0.1291 0.3884 0.5155
1.000 0.7252 0.01104 0.00361 -0.1290 0.3853 0.5192
1.250 0.7531 0.01114 0.00370 -0.1290 0.3823 0.5230
1.500 0.7816 0.01122 0.00377 -0.1290 0.3797 0.5270
1.750 0.8099 0.01131 0.00385 -0.1290 0.3768 0.5305
2.000 0.8379 0.01141 0.00393 -0.1289 0.3741 0.5337
2.250 0.8657 0.01151 0.00404 -0.1289 0.3716 0.5373
2.500 0.8933 0.01163 0.00415 -0.1288 0.3691 0.5414
2.750 0.9206 0.01177 0.00427 -0.1286 0.3667 0.5456
3.000 0.9481 0.01190 0.00441 -0.1285 0.3646 0.5496
3.250 0.9761 0.01200 0.00452 -0.1285 0.3629 0.5535
3.500 1.0038 0.01211 0.00465 -0.1284 0.3610 0.5572
3.750 1.0313 0.01222 0.00480 -0.1283 0.3590 0.5615
4.000 1.0586 0.01235 0.00494 -0.1282 0.3569 0.5666
4.250 1.0857 0.01249 0.00509 -0.1280 0.3546 0.5719
4.500 1.1125 0.01265 0.00524 -0.1278 0.3525 0.5766
4.750 1.1390 0.01280 0.00542 -0.1276 0.3506 0.5813
5.000 1.1653 0.01299 0.00562 -0.1274 0.3487 0.5866
5.250 1.1919 0.01315 0.00581 -0.1271 0.3472 0.5923
5.500 1.2188 0.01329 0.00600 -0.1270 0.3458 0.5978
5.750 1.2456 0.01343 0.00619 -0.1268 0.3444 0.6040
6.000 1.2721 0.01357 0.00640 -0.1266 0.3426 0.6111
6.250 1.2982 0.01374 0.00660 -0.1263 0.3407 0.6181
6.500 1.3241 0.01390 0.00682 -0.1260 0.3389 0.6250
6.750 1.3497 0.01409 0.00704 -0.1257 0.3372 0.6325
7.250 1.3995 0.01450 0.00752 -0.1248 0.3332 0.6479
7.500 1.4236 0.01476 0.00780 -0.1242 0.3309 0.6566
7.750 1.4488 0.01491 0.00805 -0.1238 0.3291 0.6656
8.000 1.4736 0.01507 0.00829 -0.1234 0.3267 0.6762
8.250 1.4978 0.01523 0.00853 -0.1228 0.3237 0.6867
8.500 1.5209 0.01543 0.00878 -0.1221 0.3205 0.6982
8.750 1.5430 0.01566 0.00906 -0.1212 0.3174 0.7093
9.250 1.5853 0.01611 0.00964 -0.1191 0.3117 0.7346
9.500 1.6062 0.01629 0.00993 -0.1180 0.3082 0.7489
9.750 1.6256 0.01652 0.01024 -0.1166 0.3047 0.7657
10.000 1.6438 0.01679 0.01058 -0.1151 0.3014 0.7852
10.250 1.6600 0.01712 0.01097 -0.1133 0.2979 0.8073
10.500 1.6791 0.01731 0.01132 -0.1119 0.2948 0.8339
10.750 1.6953 0.01753 0.01168 -0.1100 0.2908 0.8844
11.000 1.7081 0.01776 0.01201 -0.1076 0.2865 0.9879
11.250 1.7233 0.01824 0.01250 -0.1059 0.2821 1.0000
11.500 1.7417 0.01863 0.01296 -0.1047 0.2768 1.0000
11.750 1.7556 0.01919 0.01353 -0.1030 0.2702 1.0000
12.000 1.7691 0.01980 0.01417 -0.1013 0.2637 1.0000
12.250 1.7801 0.02055 0.01493 -0.0994 0.2552 1.0000
12.500 1.7892 0.02144 0.01583 -0.0974 0.2458 1.0000
12.750 1.7935 0.02264 0.01701 -0.0950 0.2349 1.0000
13.000 1.7939 0.02418 0.01853 -0.0925 0.2226 1.0000
13.250 1.7901 0.02614 0.02046 -0.0900 0.2102 1.0000
13.500 1.7850 0.02839 0.02270 -0.0879 0.1983 1.0000
13.750 1.7785 0.03096 0.02527 -0.0860 0.1876 1.0000
14.000 1.7696 0.03394 0.02828 -0.0845 0.1781 1.0000
14.500 1.7484 0.04091 0.03530 -0.0824 0.1607 1.0000
14.750 1.7351 0.04499 0.03943 -0.0819 0.1538 1.0000
15.000 1.7221 0.04923 0.04372 -0.0817 0.1467 1.0000
15.250 1.7070 0.05392 0.04848 -0.0818 0.1408 1.0000
15.500 1.6923 0.05874 0.05336 -0.0821 0.1347 1.0000
15.750 1.6767 0.06389 0.05858 -0.0828 0.1299 1.0000
16.000 1.6629 0.06895 0.06371 -0.0835 0.1245 1.0000
16.500 1.6349 0.07960 0.07449 -0.0857 0.1151 1.0000
16.750 1.6211 0.08505 0.08000 -0.0870 0.1104 1.0000
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