NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 200,000 Max Cl/Cd: 89.49 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s803-nr-200000.txt Download as CSV file: xf-s803-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S803 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3587 0.10496 0.10146 -0.0434 1.0000 0.0501
-9.250 -0.3733 0.10188 0.09847 -0.0460 1.0000 0.0506
-9.000 -0.3837 0.09886 0.09552 -0.0468 1.0000 0.0508
-8.750 -0.3853 0.09410 0.09082 -0.0446 1.0000 0.0517
-8.500 -0.3777 0.09230 0.08904 -0.0414 1.0000 0.0528
-8.250 -0.3757 0.09094 0.08772 -0.0387 1.0000 0.0544
-8.000 -0.3844 0.08928 0.08613 -0.0365 1.0000 0.0558
-7.750 -0.4009 0.08771 0.08466 -0.0339 1.0000 0.0562
-7.500 -0.3938 0.08318 0.08015 -0.0405 0.9951 0.0596
-7.250 -0.3782 0.06807 0.06454 -0.0781 0.9752 0.0627
-7.000 -0.3592 0.06335 0.06015 -0.0753 0.9741 0.0649
-6.750 -0.3361 0.06036 0.05713 -0.0777 0.9673 0.0672
-6.250 -0.2846 0.04722 0.04337 -0.0960 0.9509 0.0785
-6.000 -0.2499 0.04402 0.04010 -0.1000 0.9480 0.0828
-5.750 -0.2124 0.03185 0.02612 -0.1073 0.9383 0.0512
-5.500 -0.1754 0.02673 0.02074 -0.1109 0.9357 0.0474
-5.250 -0.1394 0.02315 0.01656 -0.1130 0.9303 0.0445
-5.000 -0.1024 0.02099 0.01401 -0.1148 0.9252 0.0442
-4.750 -0.0620 0.01947 0.01233 -0.1173 0.9223 0.0458
-4.500 -0.0196 0.01821 0.01092 -0.1200 0.9202 0.0484
-4.250 0.0126 0.01713 0.00972 -0.1207 0.9120 0.0497
-4.000 0.0537 0.01579 0.00834 -0.1233 0.9082 0.0520
-3.750 0.0973 0.01467 0.00727 -0.1266 0.9051 0.0577
-3.500 0.1303 0.01390 0.00650 -0.1278 0.8955 0.0669
-3.250 0.1745 0.01236 0.00543 -0.1318 0.8909 0.1654
-3.000 0.2088 0.01124 0.00507 -0.1341 0.8813 0.3637
-2.750 0.2452 0.01064 0.00523 -0.1357 0.8748 0.5884
-2.500 0.2733 0.01086 0.00546 -0.1351 0.8637 0.6549
-2.250 0.3022 0.01109 0.00563 -0.1346 0.8541 0.6900
-2.000 0.3317 0.01126 0.00573 -0.1342 0.8457 0.7123
-1.750 0.3562 0.01147 0.00589 -0.1329 0.8354 0.7312
-1.500 0.3836 0.01162 0.00596 -0.1322 0.8272 0.7471
-1.250 0.4088 0.01175 0.00602 -0.1312 0.8179 0.7605
-1.000 0.4346 0.01188 0.00608 -0.1304 0.8097 0.7733
-0.750 0.4616 0.01198 0.00610 -0.1300 0.8019 0.7852
-0.500 0.4858 0.01208 0.00617 -0.1289 0.7943 0.7953
-0.250 0.5111 0.01216 0.00620 -0.1280 0.7868 0.8052
0.000 0.5378 0.01226 0.00625 -0.1277 0.7801 0.8156
0.250 0.5615 0.01233 0.00630 -0.1266 0.7730 0.8246
0.500 0.5886 0.01240 0.00631 -0.1263 0.7673 0.8334
0.750 0.6130 0.01248 0.00640 -0.1256 0.7599 0.8416
1.000 0.6409 0.01253 0.00640 -0.1255 0.7544 0.8480
1.250 0.6660 0.01261 0.00650 -0.1250 0.7478 0.8545
1.500 0.6941 0.01268 0.00654 -0.1252 0.7415 0.8606
1.750 0.7209 0.01274 0.00658 -0.1249 0.7358 0.8661
2.000 0.7473 0.01283 0.00670 -0.1248 0.7286 0.8723
2.250 0.7758 0.01286 0.00669 -0.1248 0.7228 0.8774
2.500 0.7998 0.01293 0.00682 -0.1241 0.7148 0.8836
2.750 0.8289 0.01297 0.00683 -0.1244 0.7080 0.8895
3.000 0.8519 0.01300 0.00692 -0.1234 0.6994 0.8959
3.250 0.8812 0.01301 0.00688 -0.1236 0.6918 0.9029
3.500 0.9025 0.01299 0.00694 -0.1222 0.6818 0.9107
3.750 0.9287 0.01298 0.00695 -0.1217 0.6729 0.9188
4.000 0.9530 0.01293 0.00693 -0.1209 0.6633 0.9292
4.250 0.9754 0.01288 0.00695 -0.1196 0.6533 0.9429
4.500 1.0039 0.01281 0.00690 -0.1197 0.6429 0.9631
4.750 1.0369 0.01283 0.00695 -0.1209 0.6312 1.0000
5.000 1.0664 0.01293 0.00710 -0.1214 0.6186 1.0000
5.250 1.0955 0.01302 0.00723 -0.1219 0.6050 1.0000
5.500 1.1238 0.01311 0.00736 -0.1221 0.5901 1.0000
5.750 1.1508 0.01321 0.00748 -0.1221 0.5736 1.0000
6.000 1.1766 0.01332 0.00757 -0.1217 0.5543 1.0000
6.250 1.2000 0.01346 0.00777 -0.1209 0.5301 1.0000
6.500 1.2216 0.01365 0.00794 -0.1197 0.4992 1.0000
6.750 1.2397 0.01400 0.00815 -0.1179 0.4523 1.0000
7.000 1.2502 0.01479 0.00855 -0.1148 0.3825 1.0000
7.250 1.2563 0.01600 0.00932 -0.1113 0.3149 1.0000
7.500 1.2626 0.01727 0.01024 -0.1080 0.2571 1.0000
7.750 1.2687 0.01852 0.01119 -0.1046 0.2118 1.0000
8.000 1.2749 0.01969 0.01216 -0.1014 0.1783 1.0000
8.250 1.2813 0.02090 0.01319 -0.0982 0.1540 1.0000
8.500 1.2893 0.02205 0.01426 -0.0954 0.1358 1.0000
8.750 1.2971 0.02325 0.01539 -0.0926 0.1219 1.0000
9.250 1.3148 0.02565 0.01777 -0.0878 0.1019 1.0000
9.500 1.3224 0.02706 0.01918 -0.0853 0.0949 1.0000
9.750 1.3327 0.02828 0.02043 -0.0834 0.0885 1.0000
10.000 1.3408 0.02985 0.02200 -0.0813 0.0831 1.0000
10.250 1.3525 0.03108 0.02332 -0.0796 0.0781 1.0000
10.500 1.3621 0.03269 0.02490 -0.0779 0.0739 1.0000
10.750 1.3749 0.03420 0.02650 -0.0765 0.0702 1.0000
11.000 1.3871 0.03554 0.02796 -0.0751 0.0665 1.0000
11.250 1.3988 0.03704 0.02947 -0.0738 0.0633 1.0000
11.500 1.4165 0.03890 0.03134 -0.0729 0.0600 1.0000
11.750 1.4278 0.04037 0.03300 -0.0716 0.0574 1.0000
12.000 1.4387 0.04193 0.03469 -0.0703 0.0548 1.0000
12.250 1.4508 0.04357 0.03636 -0.0693 0.0524 1.0000
12.500 1.4694 0.04586 0.03874 -0.0687 0.0496 1.0000
12.750 1.4749 0.04771 0.04082 -0.0672 0.0478 1.0000
13.000 1.4810 0.04969 0.04298 -0.0660 0.0457 1.0000
13.250 1.4864 0.05165 0.04503 -0.0650 0.0438 1.0000
13.500 1.4983 0.05395 0.04730 -0.0644 0.0413 1.0000
13.750 1.4980 0.05687 0.05052 -0.0632 0.0399 1.0000
14.000 1.4959 0.05963 0.05353 -0.0622 0.0384 1.0000
14.250 1.4946 0.06244 0.05653 -0.0615 0.0369 1.0000
14.500 1.4937 0.06518 0.05939 -0.0611 0.0354 1.0000
14.750 1.4966 0.06775 0.06198 -0.0609 0.0340 1.0000
15.000 1.4932 0.07222 0.06663 -0.0606 0.0326 1.0000
15.250 1.4814 0.07646 0.07118 -0.0608 0.0319 1.0000
15.500 1.4691 0.08118 0.07617 -0.0614 0.0311 1.0000
15.750 1.4572 0.08608 0.08133 -0.0625 0.0302 1.0000
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