NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 100,000 Max Cl/Cd: 60.23 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s802-nr-100000-n5.txt Download as CSV file: xf-s802-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S802 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3460 0.10883 0.10397 -0.0439 1.0000 0.0564
-9.250 -0.3534 0.10635 0.10159 -0.0429 1.0000 0.0558
-8.750 -0.3622 0.08980 0.08507 -0.0564 0.9903 0.0323
-8.500 -0.3494 0.08515 0.08043 -0.0610 0.9845 0.0319
-8.250 -0.3439 0.07933 0.07462 -0.0671 0.9748 0.0319
-8.000 -0.3417 0.07307 0.06837 -0.0741 0.9630 0.0318
-7.750 -0.3367 0.06523 0.06046 -0.0843 0.9501 0.0315
-7.500 -0.3332 0.05780 0.05278 -0.0920 0.9381 0.0315
-7.250 -0.3252 0.05126 0.04589 -0.0978 0.9282 0.0315
-7.000 -0.3085 0.04547 0.03964 -0.1025 0.9214 0.0314
-6.750 -0.2918 0.04085 0.03454 -0.1050 0.9133 0.0314
-6.500 -0.2669 0.03652 0.02963 -0.1079 0.9081 0.0315
-6.250 -0.2353 0.03280 0.02524 -0.1109 0.9051 0.0318
-6.000 -0.2120 0.03039 0.02228 -0.1112 0.8975 0.0326
-5.750 -0.1810 0.02858 0.02034 -0.1131 0.8936 0.0344
-5.500 -0.1464 0.02689 0.01837 -0.1151 0.8908 0.0361
-5.250 -0.1200 0.02538 0.01657 -0.1152 0.8844 0.0370
-5.000 -0.0891 0.02396 0.01489 -0.1160 0.8799 0.0381
-4.750 -0.0556 0.02269 0.01340 -0.1172 0.8768 0.0396
-4.500 -0.0254 0.02166 0.01230 -0.1180 0.8728 0.0421
-4.250 0.0008 0.02101 0.01163 -0.1180 0.8669 0.0456
-4.000 0.0327 0.02022 0.01071 -0.1190 0.8631 0.0490
-3.750 0.0669 0.01934 0.00978 -0.1205 0.8603 0.0538
-3.500 0.0918 0.01889 0.00926 -0.1202 0.8539 0.0617
-3.250 0.1218 0.01821 0.00869 -0.1210 0.8496 0.0845
-3.000 0.1542 0.01746 0.00821 -0.1223 0.8465 0.1473
-2.750 0.1837 0.01654 0.00800 -0.1236 0.8429 0.3033
-2.500 0.2047 0.01578 0.00812 -0.1228 0.8372 0.5072
-2.250 0.2243 0.01577 0.00856 -0.1200 0.8330 0.6457
-2.000 0.2526 0.01594 0.00867 -0.1194 0.8300 0.7147
-1.750 0.2717 0.01626 0.00891 -0.1173 0.8244 0.7494
-1.500 0.2939 0.01647 0.00902 -0.1157 0.8199 0.7753
-1.250 0.3192 0.01658 0.00903 -0.1146 0.8165 0.7980
-1.000 0.3430 0.01667 0.00904 -0.1133 0.8130 0.8170
-0.750 0.3581 0.01689 0.00922 -0.1106 0.8072 0.8334
-0.500 0.3797 0.01696 0.00923 -0.1090 0.8033 0.8496
-0.250 0.4043 0.01694 0.00913 -0.1079 0.8003 0.8652
0.000 0.4219 0.01705 0.00921 -0.1058 0.7955 0.8799
0.250 0.4397 0.01715 0.00929 -0.1037 0.7905 0.8941
0.500 0.4643 0.01713 0.00923 -0.1029 0.7870 0.9070
0.750 0.4935 0.01707 0.00911 -0.1031 0.7844 0.9183
1.000 0.5112 0.01728 0.00933 -0.1014 0.7786 0.9298
1.250 0.5378 0.01736 0.00940 -0.1014 0.7742 0.9391
1.500 0.5710 0.01736 0.00938 -0.1026 0.7710 0.9472
1.750 0.6083 0.01732 0.00931 -0.1045 0.7685 0.9545
2.000 0.6322 0.01768 0.00972 -0.1045 0.7614 0.9676
2.250 0.6682 0.01774 0.00978 -0.1064 0.7572 0.9823
2.500 0.7051 0.01770 0.00975 -0.1083 0.7539 1.0000
2.750 0.7254 0.01811 0.01020 -0.1076 0.7466 1.0000
3.000 0.7575 0.01818 0.01029 -0.1086 0.7414 1.0000
3.250 0.7907 0.01821 0.01035 -0.1097 0.7362 1.0000
3.500 0.8155 0.01843 0.01062 -0.1094 0.7278 1.0000
3.750 0.8516 0.01828 0.01049 -0.1108 0.7216 1.0000
4.000 0.8766 0.01841 0.01070 -0.1104 0.7116 1.0000
4.250 0.9051 0.01841 0.01075 -0.1105 0.7017 1.0000
4.500 0.9408 0.01813 0.01049 -0.1116 0.6924 1.0000
4.750 0.9644 0.01820 0.01064 -0.1108 0.6795 1.0000
5.000 0.9895 0.01821 0.01074 -0.1101 0.6660 1.0000
5.250 1.0146 0.01820 0.01080 -0.1095 0.6513 1.0000
5.500 1.0390 0.01819 0.01085 -0.1087 0.6349 1.0000
5.750 1.0630 0.01818 0.01093 -0.1077 0.6163 1.0000
6.000 1.0803 0.01838 0.01123 -0.1058 0.5929 1.0000
6.250 1.0988 0.01851 0.01140 -0.1040 0.5627 1.0000
6.500 1.1191 0.01858 0.01137 -0.1023 0.5174 1.0000
6.750 1.1369 0.01890 0.01133 -0.1001 0.4547 1.0000
7.000 1.1452 0.01976 0.01180 -0.0967 0.3944 1.0000
7.250 1.1504 0.02085 0.01257 -0.0932 0.3412 1.0000
7.500 1.1552 0.02207 0.01350 -0.0899 0.2941 1.0000
7.750 1.1613 0.02330 0.01451 -0.0870 0.2546 1.0000
8.000 1.1688 0.02454 0.01557 -0.0844 0.2205 1.0000
8.250 1.1772 0.02578 0.01669 -0.0821 0.1920 1.0000
8.500 1.1860 0.02706 0.01785 -0.0800 0.1693 1.0000
8.750 1.1962 0.02830 0.01903 -0.0781 0.1499 1.0000
9.000 1.2062 0.02959 0.02028 -0.0762 0.1343 1.0000
9.250 1.2163 0.03092 0.02159 -0.0745 0.1218 1.0000
9.500 1.2259 0.03232 0.02300 -0.0728 0.1117 1.0000
9.750 1.2357 0.03374 0.02443 -0.0713 0.1025 1.0000
10.000 1.2465 0.03514 0.02590 -0.0698 0.0949 1.0000
10.250 1.2553 0.03671 0.02748 -0.0683 0.0888 1.0000
10.500 1.2663 0.03819 0.02906 -0.0670 0.0829 1.0000
10.750 1.2763 0.03976 0.03069 -0.0657 0.0777 1.0000
11.000 1.2855 0.04149 0.03246 -0.0644 0.0738 1.0000
11.250 1.2976 0.04304 0.03417 -0.0632 0.0696 1.0000
11.500 1.3075 0.04473 0.03594 -0.0622 0.0660 1.0000
11.750 1.3166 0.04662 0.03783 -0.0611 0.0629 1.0000
12.000 1.3291 0.04830 0.03974 -0.0601 0.0596 1.0000
12.250 1.3401 0.05012 0.04170 -0.0591 0.0568 1.0000
12.500 1.3488 0.05205 0.04371 -0.0583 0.0543 1.0000
12.750 1.3582 0.05417 0.04588 -0.0574 0.0519 1.0000
13.000 1.3676 0.05631 0.04831 -0.0565 0.0496 1.0000
13.250 1.3757 0.05859 0.05081 -0.0557 0.0474 1.0000
13.500 1.3809 0.06097 0.05334 -0.0550 0.0454 1.0000
13.750 1.3852 0.06341 0.05586 -0.0544 0.0437 1.0000
14.000 1.3900 0.06618 0.05874 -0.0539 0.0421 1.0000
14.250 1.3901 0.06947 0.06239 -0.0533 0.0407 1.0000
14.500 1.3879 0.07298 0.06619 -0.0530 0.0392 1.0000
14.750 1.3843 0.07658 0.07006 -0.0530 0.0378 1.0000
15.000 1.3804 0.08021 0.07387 -0.0532 0.0366 1.0000
15.250 1.3774 0.08377 0.07754 -0.0536 0.0355 1.0000
15.500 1.3756 0.08736 0.08120 -0.0541 0.0345 1.0000
15.750 1.3646 0.09255 0.08666 -0.0553 0.0338 1.0000
16.000 1.3487 0.09868 0.09313 -0.0573 0.0332 1.0000
16.250 1.3310 0.10541 0.10018 -0.0600 0.0327 1.0000
16.500 1.3114 0.11289 0.10795 -0.0636 0.0323 1.0000
16.750 1.2893 0.12138 0.11672 -0.0683 0.0321 1.0000
17.000 1.2635 0.13139 0.12698 -0.0746 0.0322 1.0000
17.250 1.2323 0.14368 0.13951 -0.0829 0.0326 1.0000
17.500 1.1933 0.15960 0.15557 -0.0939 0.0334 1.0000
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