NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 100,000 Max Cl/Cd: 63.12 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s803-nr-100000.txt Download as CSV file: xf-s803-nr-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3442 0.10854 0.10363 -0.0404 1.0000 0.1012
-9.000 -0.3695 0.10739 0.10264 -0.0431 1.0000 0.1032
-8.750 -0.3970 0.10616 0.10157 -0.0444 1.0000 0.1037
-8.500 -0.3531 0.09990 0.09521 -0.0393 1.0000 0.1075
-8.250 -0.3519 0.09761 0.09297 -0.0378 1.0000 0.1107
-8.000 -0.3617 0.09560 0.09106 -0.0368 1.0000 0.1143
-7.750 -0.3873 0.09445 0.09006 -0.0357 1.0000 0.1168
-7.500 -0.4220 0.09402 0.08981 -0.0331 1.0000 0.1175
-7.250 -0.4544 0.09257 0.08853 -0.0339 1.0000 0.1180
-7.000 -0.4883 0.08959 0.08556 -0.0399 1.0000 0.1185
-6.750 -0.4591 0.08753 0.08360 -0.0265 1.0000 0.1214
-6.500 -0.4621 0.08608 0.08221 -0.0232 1.0000 0.1243
-6.250 -0.4553 0.07710 0.07310 -0.0455 0.9904 0.1346
-6.000 -0.4292 0.07650 0.07261 -0.0381 0.9873 0.1417
-5.750 -0.4045 0.07040 0.06642 -0.0484 0.9780 0.1539
-5.500 -0.3777 0.06502 0.06092 -0.0571 0.9696 0.1680
-5.250 -0.3485 0.06051 0.05629 -0.0634 0.9621 0.1836
-5.000 -0.2829 0.04103 0.03483 -0.0864 0.9563 0.0867
-4.750 -0.2353 0.03567 0.02832 -0.0915 0.9515 0.0752
-4.500 -0.1896 0.03275 0.02482 -0.0957 0.9480 0.0755
-4.250 -0.1570 0.03029 0.02200 -0.0972 0.9407 0.0751
-4.000 -0.1141 0.02832 0.01962 -0.1001 0.9362 0.0756
-3.750 -0.0791 0.02637 0.01761 -0.1018 0.9304 0.0785
-3.500 -0.0427 0.02533 0.01651 -0.1035 0.9239 0.0850
-3.250 0.0001 0.02398 0.01514 -0.1061 0.9203 0.0928
-3.000 0.0278 0.02325 0.01444 -0.1062 0.9119 0.1044
-2.750 0.0704 0.02151 0.01329 -0.1095 0.9079 0.1818
-2.500 0.1062 0.01985 0.01367 -0.1110 0.9045 0.6250
-2.250 0.1208 0.02058 0.01445 -0.1070 0.8944 0.7086
-2.000 0.1468 0.02092 0.01474 -0.1046 0.8896 0.7550
-1.750 0.1571 0.02134 0.01510 -0.1004 0.8797 0.7846
-1.500 0.1815 0.02130 0.01499 -0.0979 0.8756 0.8160
-1.250 0.1865 0.02157 0.01523 -0.0931 0.8652 0.8386
-1.000 0.2102 0.02133 0.01489 -0.0910 0.8612 0.8647
-0.750 0.2153 0.02159 0.01510 -0.0868 0.8516 0.8865
-0.500 0.2382 0.02125 0.01467 -0.0849 0.8470 0.9100
-0.250 0.2507 0.02137 0.01474 -0.0822 0.8392 0.9328
0.000 0.2840 0.02125 0.01455 -0.0831 0.8342 0.9588
0.250 0.3531 0.02097 0.01414 -0.0908 0.8325 0.9838
0.500 0.4143 0.02072 0.01376 -0.0973 0.8306 1.0000
0.750 0.4139 0.02150 0.01451 -0.0941 0.8196 1.0000
1.000 0.4594 0.02139 0.01432 -0.0978 0.8164 1.0000
1.250 0.4796 0.02204 0.01493 -0.0979 0.8084 1.0000
1.500 0.5175 0.02219 0.01503 -0.1004 0.8032 1.0000
1.750 0.5645 0.02201 0.01480 -0.1040 0.8003 1.0000
2.000 0.5827 0.02291 0.01571 -0.1039 0.7909 1.0000
2.250 0.6258 0.02284 0.01562 -0.1068 0.7867 1.0000
2.500 0.6747 0.02252 0.01529 -0.1104 0.7839 1.0000
2.750 0.6907 0.02353 0.01634 -0.1098 0.7731 1.0000
3.000 0.7392 0.02313 0.01594 -0.1131 0.7696 1.0000
3.250 0.7593 0.02396 0.01680 -0.1129 0.7593 1.0000
3.500 0.8077 0.02343 0.01631 -0.1158 0.7547 1.0000
3.750 0.8312 0.02401 0.01695 -0.1157 0.7443 1.0000
4.000 0.8814 0.02321 0.01617 -0.1186 0.7387 1.0000
4.250 0.9072 0.02352 0.01656 -0.1184 0.7272 1.0000
4.500 0.9435 0.02321 0.01630 -0.1192 0.7171 1.0000
4.750 0.9893 0.02235 0.01546 -0.1210 0.7076 1.0000
5.000 1.0179 0.02227 0.01547 -0.1207 0.6944 1.0000
5.250 1.0488 0.02204 0.01529 -0.1206 0.6808 1.0000
5.500 1.0803 0.02171 0.01501 -0.1204 0.6666 1.0000
5.750 1.1114 0.02134 0.01472 -0.1201 0.6512 1.0000
6.000 1.1418 0.02096 0.01438 -0.1197 0.6347 1.0000
6.250 1.1719 0.02053 0.01398 -0.1191 0.6165 1.0000
6.500 1.1955 0.02032 0.01387 -0.1177 0.5955 1.0000
6.750 1.2191 0.02003 0.01362 -0.1161 0.5712 1.0000
7.000 1.2378 0.01988 0.01354 -0.1137 0.5416 1.0000
7.250 1.2529 0.01985 0.01354 -0.1108 0.5022 1.0000
7.500 1.2633 0.02004 0.01361 -0.1072 0.4434 1.0000
7.750 1.2653 0.02100 0.01399 -0.1024 0.3634 1.0000
8.000 1.2619 0.02269 0.01510 -0.0975 0.2971 1.0000
8.250 1.2592 0.02443 0.01642 -0.0929 0.2507 1.0000
8.500 1.2603 0.02616 0.01784 -0.0891 0.2165 1.0000
8.750 1.2654 0.02786 0.01929 -0.0861 0.1909 1.0000
9.000 1.2742 0.02949 0.02076 -0.0837 0.1710 1.0000
9.250 1.2862 0.03113 0.02226 -0.0818 0.1548 1.0000
9.500 1.3015 0.03273 0.02378 -0.0804 0.1411 1.0000
9.750 1.3204 0.03435 0.02541 -0.0794 0.1296 1.0000
10.000 1.3417 0.03609 0.02715 -0.0788 0.1195 1.0000
10.250 1.3730 0.03813 0.02904 -0.0797 0.1103 1.0000
10.500 1.3904 0.03978 0.03097 -0.0784 0.1037 1.0000
10.750 1.4236 0.04219 0.03332 -0.0798 0.0964 1.0000
11.000 1.4405 0.04422 0.03567 -0.0785 0.0918 1.0000
11.250 1.4646 0.04639 0.03785 -0.0786 0.0866 1.0000
11.500 1.4808 0.04935 0.04111 -0.0777 0.0828 1.0000
11.750 1.4860 0.05183 0.04400 -0.0751 0.0801 1.0000
12.000 1.4944 0.05416 0.04654 -0.0731 0.0769 1.0000
12.250 1.5211 0.05837 0.05071 -0.0746 0.0725 1.0000
12.500 1.5075 0.06078 0.05355 -0.0700 0.0717 1.0000
12.750 1.4928 0.06378 0.05695 -0.0661 0.0708 1.0000
13.000 1.4761 0.06721 0.06076 -0.0629 0.0699 1.0000
13.250 1.4578 0.07106 0.06496 -0.0603 0.0691 1.0000
13.500 1.4375 0.07534 0.06957 -0.0584 0.0684 1.0000
13.750 1.4150 0.08015 0.07469 -0.0574 0.0679 1.0000
14.000 1.3894 0.08566 0.08050 -0.0572 0.0677 1.0000
14.250 1.3602 0.09208 0.08720 -0.0580 0.0681 1.0000
14.500 1.3283 0.09943 0.09482 -0.0601 0.0687 1.0000
14.750 1.2953 0.10768 0.10329 -0.0635 0.0696 1.0000
15.000 1.2630 0.11676 0.11255 -0.0681 0.0706 1.0000
15.250 1.2336 0.12649 0.12241 -0.0735 0.0716 1.0000
15.500 1.2087 0.13664 0.13263 -0.0793 0.0723 1.0000
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Polar data table (+)
Polar graphs
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