NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 500,000 Max Cl/Cd: 118.38 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s803-nr-500000.txt Download as CSV file: xf-s803-nr-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2635 0.08699 0.08492 -0.0487 0.9955 0.0250
-9.250 -0.2693 0.07815 0.07609 -0.0561 0.9939 0.0261
-8.000 -0.3634 0.05008 0.04763 -0.0951 0.9752 0.0268
-7.750 -0.3371 0.04747 0.04500 -0.0993 0.9729 0.0273
-7.500 -0.3189 0.04520 0.04268 -0.1015 0.9649 0.0280
-7.250 -0.2918 0.04099 0.03827 -0.1073 0.9612 0.0295
-7.000 -0.2748 0.03281 0.02925 -0.1138 0.9506 0.0338
-6.750 -0.2480 0.02405 0.01961 -0.1176 0.9457 0.0271
-6.500 -0.2201 0.02045 0.01571 -0.1187 0.9393 0.0240
-6.250 -0.1849 0.01764 0.01249 -0.1209 0.9360 0.0235
-6.000 -0.1507 0.01602 0.01063 -0.1225 0.9305 0.0238
-5.750 -0.1140 0.01486 0.00931 -0.1246 0.9245 0.0246
-5.500 -0.0718 0.01385 0.00815 -0.1277 0.9203 0.0255
-5.250 -0.0353 0.01296 0.00714 -0.1296 0.9108 0.0260
-5.000 0.0035 0.01194 0.00602 -0.1321 0.9016 0.0265
-4.750 0.0403 0.01099 0.00499 -0.1344 0.8902 0.0277
-4.500 0.0731 0.01052 0.00444 -0.1356 0.8761 0.0291
-4.250 0.1041 0.01019 0.00403 -0.1363 0.8615 0.0310
-4.000 0.1336 0.00990 0.00363 -0.1367 0.8468 0.0324
-3.750 0.1624 0.00954 0.00316 -0.1369 0.8325 0.0349
-3.500 0.1906 0.00933 0.00288 -0.1370 0.8189 0.0392
-3.250 0.2191 0.00896 0.00256 -0.1373 0.8064 0.0662
-3.000 0.2476 0.00842 0.00236 -0.1379 0.7950 0.1679
-2.750 0.2760 0.00807 0.00222 -0.1384 0.7841 0.2570
-2.500 0.3045 0.00763 0.00210 -0.1390 0.7732 0.3704
-2.250 0.3331 0.00717 0.00209 -0.1396 0.7635 0.5260
-2.000 0.3608 0.00718 0.00220 -0.1395 0.7541 0.6045
-1.750 0.3884 0.00726 0.00228 -0.1393 0.7452 0.6365
-1.500 0.4162 0.00740 0.00233 -0.1391 0.7375 0.6580
-1.250 0.4437 0.00750 0.00241 -0.1389 0.7292 0.6759
-1.000 0.4712 0.00763 0.00248 -0.1386 0.7221 0.6883
-0.750 0.4988 0.00769 0.00253 -0.1385 0.7145 0.6970
-0.500 0.5267 0.00781 0.00257 -0.1384 0.7082 0.7065
-0.250 0.5542 0.00787 0.00264 -0.1382 0.7018 0.7135
0.000 0.5821 0.00796 0.00268 -0.1381 0.6954 0.7209
0.250 0.6098 0.00806 0.00275 -0.1380 0.6898 0.7275
0.500 0.6374 0.00812 0.00282 -0.1379 0.6837 0.7345
0.750 0.6652 0.00822 0.00287 -0.1378 0.6780 0.7410
1.000 0.6924 0.00829 0.00296 -0.1376 0.6719 0.7478
1.250 0.7201 0.00837 0.00301 -0.1375 0.6653 0.7543
1.500 0.7472 0.00845 0.00308 -0.1373 0.6588 0.7589
1.750 0.7742 0.00849 0.00314 -0.1371 0.6513 0.7636
2.000 0.8020 0.00860 0.00319 -0.1371 0.6443 0.7680
2.250 0.8288 0.00861 0.00324 -0.1368 0.6362 0.7715
2.500 0.8557 0.00870 0.00331 -0.1366 0.6285 0.7751
2.750 0.8825 0.00874 0.00338 -0.1363 0.6202 0.7791
3.000 0.9098 0.00884 0.00345 -0.1362 0.6126 0.7831
3.250 0.9362 0.00887 0.00352 -0.1359 0.6037 0.7867
3.500 0.9626 0.00895 0.00362 -0.1356 0.5952 0.7908
3.750 0.9891 0.00903 0.00371 -0.1353 0.5863 0.7952
4.000 1.0157 0.00910 0.00380 -0.1351 0.5764 0.7997
4.250 1.0414 0.00918 0.00392 -0.1346 0.5664 0.8038
4.500 1.0670 0.00928 0.00403 -0.1341 0.5551 0.8090
4.750 1.0925 0.00939 0.00415 -0.1337 0.5409 0.8147
5.000 1.1168 0.00949 0.00428 -0.1329 0.5247 0.8199
5.250 1.1412 0.00964 0.00444 -0.1323 0.5051 0.8262
5.500 1.1638 0.00985 0.00460 -0.1313 0.4761 0.8326
5.750 1.1829 0.01027 0.00485 -0.1296 0.4260 0.8401
6.000 1.1978 0.01103 0.00530 -0.1274 0.3617 0.8487
6.250 1.2127 0.01188 0.00586 -0.1252 0.3019 0.8592
6.500 1.2277 0.01264 0.00640 -0.1231 0.2523 0.8709
6.750 1.2428 0.01332 0.00691 -0.1209 0.2118 0.8863
7.000 1.2559 0.01387 0.00738 -0.1183 0.1794 0.9127
7.250 1.2706 0.01441 0.00783 -0.1160 0.1520 1.0000
7.500 1.2896 0.01507 0.00838 -0.1148 0.1293 1.0000
7.750 1.3071 0.01576 0.00895 -0.1133 0.1113 1.0000
8.000 1.3236 0.01639 0.00951 -0.1115 0.0974 1.0000
8.250 1.3390 0.01703 0.01010 -0.1095 0.0863 1.0000
8.500 1.3551 0.01762 0.01069 -0.1077 0.0782 1.0000
8.750 1.3689 0.01833 0.01138 -0.1055 0.0711 1.0000
9.000 1.3839 0.01896 0.01203 -0.1035 0.0655 1.0000
9.250 1.3953 0.01982 0.01288 -0.1010 0.0602 1.0000
9.500 1.4109 0.02043 0.01355 -0.0993 0.0566 1.0000
9.750 1.4225 0.02128 0.01441 -0.0970 0.0529 1.0000
10.000 1.4307 0.02237 0.01554 -0.0944 0.0496 1.0000
10.250 1.4451 0.02309 0.01634 -0.0927 0.0473 1.0000
10.500 1.4574 0.02397 0.01727 -0.0908 0.0449 1.0000
10.750 1.4649 0.02520 0.01852 -0.0884 0.0425 1.0000
11.000 1.4688 0.02676 0.02014 -0.0858 0.0405 1.0000
11.250 1.4826 0.02763 0.02112 -0.0844 0.0390 1.0000
11.500 1.4948 0.02865 0.02219 -0.0830 0.0370 1.0000
11.750 1.5049 0.02986 0.02343 -0.0815 0.0351 1.0000
12.000 1.5057 0.03191 0.02553 -0.0793 0.0331 1.0000
12.250 1.5165 0.03317 0.02689 -0.0780 0.0319 1.0000
12.500 1.5272 0.03448 0.02829 -0.0769 0.0306 1.0000
12.750 1.5368 0.03592 0.02980 -0.0758 0.0293 1.0000
13.000 1.5445 0.03758 0.03152 -0.0747 0.0280 1.0000
13.250 1.5459 0.03992 0.03392 -0.0734 0.0267 1.0000
13.500 1.5473 0.04237 0.03647 -0.0722 0.0257 1.0000
13.750 1.5564 0.04406 0.03828 -0.0715 0.0248 1.0000
14.000 1.5639 0.04595 0.04027 -0.0709 0.0236 1.0000
14.250 1.5710 0.04794 0.04233 -0.0704 0.0225 1.0000
14.500 1.5743 0.05041 0.04485 -0.0699 0.0215 1.0000
14.750 1.5666 0.05425 0.04877 -0.0693 0.0203 1.0000
15.000 1.5753 0.05623 0.05089 -0.0692 0.0195 1.0000
15.250 1.5809 0.05864 0.05341 -0.0691 0.0185 1.0000
15.500 1.5850 0.06129 0.05615 -0.0692 0.0175 1.0000
15.750 1.5845 0.06461 0.05953 -0.0694 0.0166 1.0000
16.000 1.5741 0.06939 0.06441 -0.0699 0.0158 1.0000
16.250 1.5771 0.07247 0.06764 -0.0704 0.0151 1.0000
16.500 1.5769 0.07608 0.07138 -0.0710 0.0143 1.0000
16.750 1.5753 0.07997 0.07538 -0.0720 0.0136 1.0000
17.000 1.5711 0.08437 0.07987 -0.0732 0.0131 1.0000
17.250 1.5613 0.08979 0.08539 -0.0748 0.0126 1.0000
17.500 1.5484 0.09589 0.09162 -0.0769 0.0122 1.0000
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