NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S801 Airfoil (s801-nr) Reynolds number: 500,000 Max Cl/Cd: 112.03 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s801-nr-500000-n5.txt Download as CSV file: xf-s801-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S801 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5730 0.04155 0.03848 -0.1101 0.9674 0.0103
-11.250 -0.5852 0.03693 0.03359 -0.1129 0.9482 0.0105
-11.000 -0.5837 0.03211 0.02834 -0.1180 0.9322 0.0107
-10.750 -0.5569 0.02822 0.02397 -0.1247 0.9209 0.0111
-10.500 -0.5215 0.02587 0.02121 -0.1300 0.9089 0.0115
-10.250 -0.4922 0.02374 0.01880 -0.1335 0.8928 0.0119
-10.000 -0.4659 0.02271 0.01760 -0.1349 0.8760 0.0121
-9.750 -0.4440 0.02193 0.01665 -0.1351 0.8603 0.0124
-9.500 -0.4245 0.02102 0.01554 -0.1347 0.8463 0.0127
-9.250 -0.4047 0.02022 0.01457 -0.1341 0.8343 0.0130
-9.000 -0.3847 0.01937 0.01352 -0.1335 0.8239 0.0133
-8.750 -0.3639 0.01860 0.01258 -0.1329 0.8141 0.0137
-8.500 -0.3424 0.01788 0.01170 -0.1324 0.8056 0.0141
-8.250 -0.3201 0.01725 0.01090 -0.1318 0.7974 0.0144
-8.000 -0.2965 0.01680 0.01031 -0.1315 0.7901 0.0148
-7.750 -0.2744 0.01603 0.00942 -0.1310 0.7828 0.0152
-7.500 -0.2516 0.01538 0.00870 -0.1306 0.7765 0.0157
-7.250 -0.2277 0.01487 0.00813 -0.1303 0.7704 0.0161
-7.000 -0.2034 0.01441 0.00759 -0.1300 0.7651 0.0166
-6.750 -0.1785 0.01395 0.00707 -0.1298 0.7602 0.0170
-6.500 -0.1534 0.01354 0.00659 -0.1297 0.7552 0.0175
-6.250 -0.1280 0.01315 0.00612 -0.1295 0.7507 0.0180
-6.000 -0.1019 0.01282 0.00571 -0.1295 0.7467 0.0186
-5.750 -0.0757 0.01248 0.00533 -0.1295 0.7424 0.0192
-5.500 -0.0498 0.01204 0.00485 -0.1295 0.7382 0.0202
-5.250 -0.0232 0.01175 0.00451 -0.1295 0.7344 0.0209
-5.000 0.0039 0.01149 0.00420 -0.1296 0.7308 0.0218
-4.750 0.0312 0.01125 0.00392 -0.1297 0.7273 0.0227
-4.500 0.0588 0.01105 0.00367 -0.1299 0.7239 0.0238
-4.250 0.0863 0.01082 0.00341 -0.1300 0.7208 0.0259
-4.000 0.1141 0.01064 0.00320 -0.1302 0.7181 0.0294
-3.750 0.1421 0.01040 0.00301 -0.1305 0.7154 0.0392
-3.500 0.1700 0.01013 0.00284 -0.1308 0.7126 0.0634
-3.250 0.1981 0.00990 0.00270 -0.1312 0.7097 0.0920
-3.000 0.2263 0.00967 0.00257 -0.1316 0.7068 0.1263
-2.750 0.2546 0.00936 0.00245 -0.1321 0.7042 0.1852
-2.250 0.3124 0.00870 0.00226 -0.1335 0.6997 0.3343
-2.000 0.3420 0.00826 0.00216 -0.1345 0.6974 0.4440
-1.750 0.3713 0.00778 0.00217 -0.1353 0.6951 0.5830
-1.500 0.3994 0.00777 0.00235 -0.1353 0.6928 0.6592
-1.250 0.4279 0.00785 0.00241 -0.1354 0.6905 0.6787
-1.000 0.4567 0.00793 0.00245 -0.1356 0.6883 0.6922
-0.750 0.4855 0.00803 0.00251 -0.1358 0.6863 0.7034
-0.500 0.5139 0.00809 0.00257 -0.1359 0.6844 0.7106
-0.250 0.5425 0.00815 0.00263 -0.1361 0.6822 0.7182
0.000 0.5709 0.00822 0.00270 -0.1362 0.6798 0.7245
0.250 0.5991 0.00829 0.00277 -0.1363 0.6775 0.7300
0.500 0.6278 0.00837 0.00282 -0.1365 0.6752 0.7360
0.750 0.6559 0.00846 0.00289 -0.1366 0.6727 0.7406
1.000 0.6839 0.00854 0.00298 -0.1366 0.6700 0.7453
1.250 0.7118 0.00859 0.00306 -0.1367 0.6666 0.7497
1.500 0.7400 0.00865 0.00310 -0.1368 0.6629 0.7534
1.750 0.7673 0.00870 0.00316 -0.1367 0.6586 0.7558
2.000 0.7946 0.00876 0.00321 -0.1367 0.6539 0.7579
2.250 0.8215 0.00878 0.00327 -0.1365 0.6481 0.7599
2.500 0.8485 0.00883 0.00331 -0.1364 0.6421 0.7617
2.750 0.8754 0.00887 0.00336 -0.1363 0.6354 0.7636
3.000 0.9021 0.00892 0.00341 -0.1361 0.6280 0.7654
3.250 0.9286 0.00897 0.00347 -0.1359 0.6200 0.7670
3.500 0.9548 0.00904 0.00353 -0.1357 0.6109 0.7686
3.750 0.9808 0.00909 0.00361 -0.1354 0.6018 0.7701
4.000 1.0060 0.00916 0.00369 -0.1349 0.5907 0.7714
4.250 1.0306 0.00925 0.00379 -0.1343 0.5759 0.7727
4.500 1.0531 0.00940 0.00389 -0.1333 0.5517 0.7741
4.750 1.0714 0.00971 0.00404 -0.1314 0.5116 0.7759
5.000 1.0842 0.01030 0.00437 -0.1286 0.4600 0.7779
5.250 1.0961 0.01100 0.00481 -0.1258 0.4082 0.7799
5.500 1.1080 0.01171 0.00528 -0.1230 0.3597 0.7817
5.750 1.1197 0.01237 0.00574 -0.1202 0.3182 0.7834
6.000 1.1304 0.01297 0.00617 -0.1172 0.2821 0.7850
6.250 1.1416 0.01358 0.00665 -0.1143 0.2502 0.7867
6.500 1.1531 0.01422 0.00716 -0.1116 0.2202 0.7886
6.750 1.1659 0.01482 0.00766 -0.1091 0.1966 0.7907
7.000 1.1785 0.01544 0.00819 -0.1067 0.1740 0.7928
7.250 1.1912 0.01607 0.00874 -0.1044 0.1543 0.7948
7.500 1.2046 0.01670 0.00931 -0.1023 0.1375 0.7969
7.750 1.2178 0.01735 0.00990 -0.1002 0.1224 0.7989
8.000 1.2312 0.01799 0.01051 -0.0981 0.1108 0.8008
8.250 1.2443 0.01866 0.01117 -0.0961 0.1008 0.8027
8.500 1.2579 0.01932 0.01184 -0.0942 0.0916 0.8048
8.750 1.2714 0.02003 0.01255 -0.0924 0.0838 0.8071
9.250 1.2979 0.02156 0.01409 -0.0890 0.0706 0.8126
9.500 1.3103 0.02242 0.01495 -0.0873 0.0650 0.8152
9.750 1.3239 0.02320 0.01580 -0.0857 0.0608 0.8177
10.000 1.3362 0.02411 0.01673 -0.0841 0.0562 0.8204
10.250 1.3485 0.02505 0.01771 -0.0826 0.0525 0.8234
10.500 1.3616 0.02597 0.01868 -0.0812 0.0495 0.8266
10.750 1.3735 0.02701 0.01974 -0.0798 0.0464 0.8298
11.000 1.3847 0.02810 0.02089 -0.0784 0.0437 0.8331
11.250 1.3972 0.02911 0.02198 -0.0771 0.0415 0.8368
11.500 1.4089 0.03023 0.02316 -0.0758 0.0392 0.8410
12.000 1.4293 0.03276 0.02580 -0.0733 0.0355 0.8501
12.250 1.4410 0.03392 0.02706 -0.0722 0.0339 0.8561
12.500 1.4515 0.03520 0.02842 -0.0710 0.0322 0.8627
12.750 1.4606 0.03661 0.02988 -0.0698 0.0302 0.8709
13.000 1.4692 0.03809 0.03144 -0.0687 0.0286 0.8810
13.250 1.4794 0.03939 0.03286 -0.0676 0.0272 0.8968
13.500 1.4861 0.04067 0.03428 -0.0662 0.0257 1.0000
13.750 1.4949 0.04234 0.03598 -0.0654 0.0243 1.0000
14.000 1.5022 0.04420 0.03789 -0.0646 0.0231 1.0000
14.250 1.5117 0.04586 0.03964 -0.0640 0.0223 1.0000
14.500 1.5203 0.04764 0.04150 -0.0634 0.0213 1.0000
14.750 1.5281 0.04954 0.04348 -0.0628 0.0204 1.0000
15.000 1.5349 0.05158 0.04557 -0.0623 0.0195 1.0000
15.250 1.5403 0.05382 0.04787 -0.0618 0.0186 1.0000
15.500 1.5465 0.05600 0.05014 -0.0614 0.0178 1.0000
15.750 1.5528 0.05823 0.05247 -0.0611 0.0170 1.0000
16.000 1.5582 0.06059 0.05491 -0.0609 0.0161 1.0000
16.250 1.5623 0.06315 0.05756 -0.0607 0.0153 1.0000
16.500 1.5644 0.06602 0.06050 -0.0607 0.0145 1.0000
16.750 1.5684 0.06872 0.06330 -0.0608 0.0137 1.0000
17.000 1.5712 0.07162 0.06631 -0.0609 0.0130 1.0000
17.250 1.5726 0.07476 0.06953 -0.0612 0.0121 1.0000
17.500 1.5724 0.07821 0.07307 -0.0617 0.0115 1.0000
17.750 1.5720 0.08176 0.07672 -0.0623 0.0109 1.0000
18.000 1.5711 0.08546 0.08054 -0.0630 0.0104 1.0000
18.250 1.5688 0.08945 0.08465 -0.0640 0.0098 1.0000
18.500 1.5652 0.09375 0.08905 -0.0652 0.0093 1.0000
18.750 1.5596 0.09844 0.09386 -0.0667 0.0089 1.0000
19.000 1.5536 0.10332 0.09886 -0.0685 0.0085 1.0000
19.250 1.5476 0.10829 0.10398 -0.0704 0.0082 1.0000
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