NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 200,000 Max Cl/Cd: 83.8 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s803-nr-200000-n5.txt Download as CSV file: xf-s803-nr-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3772 0.09235 0.08883 -0.0439 1.0000 0.0198
-9.000 -0.3826 0.08922 0.08576 -0.0438 1.0000 0.0194
-8.750 -0.3885 0.08299 0.07958 -0.0479 0.9982 0.0200
-8.500 -0.3810 0.07645 0.07306 -0.0551 0.9934 0.0198
-8.250 -0.3766 0.06914 0.06576 -0.0635 0.9860 0.0195
-8.000 -0.3820 0.05476 0.05126 -0.0827 0.9700 0.0190
-7.750 -0.3839 0.04383 0.03984 -0.0936 0.9545 0.0187
-7.500 -0.3704 0.03594 0.03129 -0.0999 0.9446 0.0188
-7.250 -0.3477 0.03066 0.02534 -0.1036 0.9368 0.0192
-7.000 -0.3206 0.02708 0.02115 -0.1060 0.9302 0.0198
-6.750 -0.2905 0.02457 0.01809 -0.1080 0.9237 0.0209
-6.500 -0.2563 0.02276 0.01609 -0.1103 0.9199 0.0217
-6.250 -0.2272 0.02128 0.01439 -0.1112 0.9114 0.0222
-6.000 -0.1912 0.01984 0.01273 -0.1134 0.9068 0.0229
-5.750 -0.1578 0.01864 0.01135 -0.1148 0.8999 0.0237
-5.500 -0.1212 0.01756 0.01011 -0.1169 0.8937 0.0247
-5.250 -0.0847 0.01677 0.00914 -0.1188 0.8867 0.0261
-5.000 -0.0490 0.01573 0.00807 -0.1208 0.8786 0.0275
-4.750 -0.0132 0.01498 0.00727 -0.1227 0.8698 0.0287
-4.500 0.0238 0.01433 0.00653 -0.1249 0.8612 0.0303
-4.250 0.0575 0.01381 0.00588 -0.1263 0.8508 0.0321
-4.000 0.0916 0.01331 0.00532 -0.1278 0.8407 0.0355
-3.750 0.1250 0.01295 0.00486 -0.1290 0.8302 0.0410
-3.500 0.1558 0.01252 0.00441 -0.1298 0.8189 0.0525
-3.250 0.1866 0.01209 0.00407 -0.1307 0.8085 0.0860
-2.750 0.2467 0.01119 0.00362 -0.1325 0.7889 0.2346
-2.500 0.2766 0.01052 0.00348 -0.1337 0.7798 0.3890
-2.250 0.3041 0.01017 0.00367 -0.1337 0.7705 0.5494
-2.000 0.3315 0.01024 0.00376 -0.1333 0.7616 0.6076
-1.750 0.3596 0.01036 0.00380 -0.1331 0.7537 0.6396
-1.500 0.3873 0.01046 0.00383 -0.1329 0.7457 0.6608
-1.250 0.4152 0.01057 0.00385 -0.1327 0.7385 0.6770
-1.000 0.4422 0.01066 0.00390 -0.1324 0.7307 0.6904
-0.750 0.4695 0.01076 0.00394 -0.1321 0.7239 0.7014
-0.500 0.4968 0.01085 0.00398 -0.1318 0.7173 0.7121
-0.250 0.5246 0.01096 0.00402 -0.1317 0.7109 0.7230
0.000 0.5512 0.01105 0.00410 -0.1313 0.7051 0.7320
0.250 0.5782 0.01114 0.00417 -0.1310 0.6986 0.7414
0.500 0.6056 0.01124 0.00423 -0.1308 0.6933 0.7493
0.750 0.6332 0.01132 0.00429 -0.1307 0.6876 0.7557
1.000 0.6602 0.01140 0.00437 -0.1305 0.6818 0.7607
1.250 0.6885 0.01150 0.00442 -0.1306 0.6768 0.7659
1.500 0.7160 0.01158 0.00452 -0.1306 0.6709 0.7704
1.750 0.7431 0.01166 0.00461 -0.1304 0.6650 0.7743
2.000 0.7707 0.01176 0.00470 -0.1303 0.6594 0.7786
2.250 0.7979 0.01185 0.00481 -0.1302 0.6521 0.7833
2.500 0.8249 0.01195 0.00488 -0.1300 0.6454 0.7872
2.750 0.8506 0.01203 0.00503 -0.1296 0.6365 0.7916
3.000 0.8774 0.01213 0.00511 -0.1293 0.6280 0.7962
3.250 0.9034 0.01222 0.00522 -0.1289 0.6178 0.8008
3.500 0.9284 0.01230 0.00534 -0.1283 0.6069 0.8056
3.750 0.9541 0.01240 0.00547 -0.1278 0.5962 0.8112
4.000 0.9794 0.01251 0.00559 -0.1273 0.5849 0.8164
4.250 1.0036 0.01261 0.00574 -0.1265 0.5721 0.8218
4.500 1.0283 0.01273 0.00591 -0.1258 0.5585 0.8283
4.750 1.0518 0.01284 0.00607 -0.1249 0.5437 0.8348
5.000 1.0753 0.01299 0.00623 -0.1240 0.5267 0.8427
5.250 1.0975 0.01314 0.00641 -0.1229 0.5058 0.8506
5.500 1.1187 0.01335 0.00661 -0.1215 0.4775 0.8600
5.750 1.1367 0.01365 0.00681 -0.1196 0.4363 0.8710
6.000 1.1492 0.01422 0.00713 -0.1167 0.3810 0.8860
6.250 1.1585 0.01491 0.00759 -0.1134 0.3294 0.9110
6.500 1.1704 0.01564 0.00813 -0.1107 0.2825 1.0000
6.750 1.1855 0.01655 0.00881 -0.1089 0.2408 1.0000
7.000 1.2010 0.01740 0.00949 -0.1072 0.2061 1.0000
7.250 1.2162 0.01824 0.01018 -0.1054 0.1776 1.0000
7.500 1.2301 0.01905 0.01088 -0.1034 0.1543 1.0000
7.750 1.2441 0.01984 0.01160 -0.1014 0.1359 1.0000
8.000 1.2581 0.02063 0.01234 -0.0994 0.1204 1.0000
8.250 1.2716 0.02145 0.01313 -0.0974 0.1076 1.0000
8.500 1.2844 0.02231 0.01396 -0.0954 0.0972 1.0000
8.750 1.2979 0.02314 0.01481 -0.0935 0.0882 1.0000
9.000 1.3104 0.02404 0.01575 -0.0915 0.0810 1.0000
9.250 1.3219 0.02502 0.01674 -0.0895 0.0746 1.0000
9.500 1.3334 0.02602 0.01779 -0.0876 0.0698 1.0000
9.750 1.3448 0.02706 0.01889 -0.0857 0.0652 1.0000
10.000 1.3529 0.02836 0.02020 -0.0837 0.0611 1.0000
10.250 1.3645 0.02945 0.02142 -0.0820 0.0577 1.0000
10.500 1.3745 0.03070 0.02274 -0.0804 0.0544 1.0000
10.750 1.3822 0.03217 0.02425 -0.0786 0.0517 1.0000
11.000 1.3893 0.03376 0.02590 -0.0770 0.0494 1.0000
11.250 1.3991 0.03517 0.02744 -0.0756 0.0470 1.0000
11.500 1.4077 0.03672 0.02909 -0.0743 0.0447 1.0000
11.750 1.4147 0.03846 0.03090 -0.0730 0.0428 1.0000
12.000 1.4182 0.04059 0.03309 -0.0717 0.0410 1.0000
12.250 1.4265 0.04235 0.03498 -0.0707 0.0395 1.0000
12.500 1.4342 0.04418 0.03695 -0.0697 0.0378 1.0000
12.750 1.4409 0.04615 0.03904 -0.0689 0.0362 1.0000
13.000 1.4464 0.04828 0.04127 -0.0681 0.0347 1.0000
13.250 1.4492 0.05076 0.04380 -0.0674 0.0334 1.0000
13.500 1.4529 0.05323 0.04638 -0.0668 0.0322 1.0000
13.750 1.4587 0.05550 0.04883 -0.0663 0.0308 1.0000
14.000 1.4632 0.05797 0.05146 -0.0660 0.0294 1.0000
14.250 1.4667 0.06059 0.05421 -0.0658 0.0281 1.0000
14.500 1.4682 0.06351 0.05722 -0.0658 0.0270 1.0000
14.750 1.4664 0.06694 0.06070 -0.0660 0.0259 1.0000
15.000 1.4694 0.06990 0.06388 -0.0661 0.0249 1.0000
15.250 1.4704 0.07317 0.06734 -0.0665 0.0237 1.0000
15.500 1.4702 0.07667 0.07099 -0.0670 0.0227 1.0000
15.750 1.4689 0.08042 0.07487 -0.0679 0.0218 1.0000
16.000 1.4658 0.08454 0.07911 -0.0690 0.0211 1.0000
16.250 1.4601 0.08917 0.08383 -0.0704 0.0204 1.0000
16.500 1.4562 0.09369 0.08855 -0.0718 0.0197 1.0000
16.750 1.4513 0.09847 0.09356 -0.0734 0.0190 1.0000
17.000 1.4455 0.10355 0.09883 -0.0755 0.0183 1.0000
17.250 1.4388 0.10891 0.10435 -0.0778 0.0177 1.0000
17.500 1.4315 0.11454 0.11014 -0.0806 0.0171 1.0000
17.750 1.4232 0.12048 0.11622 -0.0837 0.0167 1.0000
18.000 1.4140 0.12676 0.12263 -0.0872 0.0163 1.0000
18.250 1.4040 0.13332 0.12931 -0.0910 0.0160 1.0000
18.500 1.3930 0.14027 0.13642 -0.0951 0.0157 1.0000
18.750 1.3806 0.14779 0.14415 -0.0998 0.0154 1.0000
19.000 1.3670 0.15582 0.15238 -0.1050 0.0152 1.0000
19.250 1.3517 0.16453 0.16128 -0.1109 0.0150 1.0000
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