FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 03-182 AIRFOIL (fxs03182-il) Reynolds number: 100,000 Max Cl/Cd: 28.08 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs03182-il-100000-n5.txt Download as CSV file: xf-fxs03182-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 03-182 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4049 0.09688 0.09224 -0.0775 0.9933 0.0143
-12.750 -0.4258 0.08543 0.08068 -0.0863 0.9835 0.0138
-12.500 -0.4474 0.07608 0.07114 -0.0940 0.9722 0.0136
-12.250 -0.4690 0.06794 0.06271 -0.1006 0.9612 0.0137
-12.000 -0.4765 0.06216 0.05668 -0.1057 0.9521 0.0131
-11.750 -0.4845 0.05658 0.05076 -0.1100 0.9418 0.0132
-11.500 -0.4875 0.05183 0.04563 -0.1132 0.9308 0.0132
-11.250 -0.4858 0.04768 0.04102 -0.1157 0.9203 0.0140
-11.000 -0.4749 0.04432 0.03727 -0.1177 0.9112 0.0140
-10.750 -0.4636 0.04138 0.03391 -0.1184 0.9006 0.0145
-10.500 -0.4462 0.03896 0.03109 -0.1187 0.8915 0.0150
-10.250 -0.4281 0.03699 0.02896 -0.1192 0.8832 0.0155
-10.000 -0.4131 0.03551 0.02731 -0.1189 0.8736 0.0162
-9.750 -0.3937 0.03412 0.02575 -0.1188 0.8663 0.0171
-9.500 -0.3766 0.03289 0.02436 -0.1181 0.8581 0.0182
-9.250 -0.3581 0.03162 0.02288 -0.1173 0.8515 0.0201
-9.000 -0.3438 0.03055 0.02167 -0.1163 0.8437 0.0215
-8.750 -0.3297 0.02948 0.02056 -0.1155 0.8373 0.0243
-8.500 -0.3159 0.02869 0.01965 -0.1143 0.8299 0.0279
-8.250 -0.2987 0.02790 0.01878 -0.1137 0.8246 0.0342
-8.000 -0.2867 0.02725 0.01807 -0.1122 0.8177 0.0410
-7.750 -0.2718 0.02658 0.01732 -0.1111 0.8125 0.0472
-7.500 -0.2597 0.02593 0.01660 -0.1095 0.8072 0.0521
-7.250 -0.2487 0.02542 0.01602 -0.1076 0.8016 0.0569
-7.000 -0.2357 0.02490 0.01541 -0.1060 0.7972 0.0637
-6.750 -0.2271 0.02444 0.01496 -0.1038 0.7920 0.0761
-6.500 -0.2188 0.02384 0.01448 -0.1017 0.7868 0.0950
-6.250 -0.2094 0.02307 0.01387 -0.0999 0.7828 0.1266
-6.000 -0.2074 0.02219 0.01328 -0.0971 0.7780 0.1832
-5.750 -0.2098 0.02100 0.01259 -0.0940 0.7731 0.2751
-5.500 -0.2046 0.02011 0.01252 -0.0912 0.7695 0.4206
-5.250 -0.1754 0.02126 0.01399 -0.0892 0.7674 0.5175
-5.000 -0.1589 0.02134 0.01391 -0.0881 0.7633 0.5558
-4.750 -0.1380 0.02179 0.01421 -0.0870 0.7595 0.5839
-4.500 -0.1135 0.02273 0.01500 -0.0855 0.7564 0.6105
-4.250 -0.0840 0.02434 0.01656 -0.0831 0.7542 0.6304
-4.000 -0.0553 0.02536 0.01745 -0.0815 0.7522 0.6444
-3.750 -0.0409 0.02557 0.01759 -0.0796 0.7480 0.6545
-3.500 -0.0185 0.02583 0.01774 -0.0784 0.7450 0.6582
-3.250 0.0040 0.02573 0.01749 -0.0781 0.7425 0.6638
-3.000 0.0281 0.02543 0.01704 -0.0784 0.7403 0.6689
-2.750 0.0555 0.02543 0.01691 -0.0784 0.7386 0.6715
-2.500 0.0724 0.02557 0.01699 -0.0770 0.7350 0.6754
-2.250 0.0900 0.02537 0.01668 -0.0767 0.7312 0.6823
-2.000 0.1126 0.02547 0.01672 -0.0760 0.7287 0.6844
-1.750 0.1375 0.02548 0.01665 -0.0758 0.7267 0.6868
-1.500 0.1642 0.02541 0.01648 -0.0761 0.7251 0.6897
-1.250 0.1930 0.02525 0.01621 -0.0771 0.7237 0.6932
-1.000 0.2022 0.02552 0.01647 -0.0754 0.7189 0.6974
-0.750 0.2208 0.02573 0.01666 -0.0742 0.7156 0.6995
-0.500 0.2445 0.02582 0.01670 -0.0739 0.7134 0.7018
-0.250 0.2710 0.02584 0.01668 -0.0743 0.7116 0.7043
0.000 0.2998 0.02580 0.01658 -0.0752 0.7102 0.7071
0.250 0.3179 0.02607 0.01681 -0.0749 0.7069 0.7106
0.500 0.3273 0.02661 0.01738 -0.0728 0.7021 0.7127
0.750 0.3482 0.02687 0.01765 -0.0722 0.6996 0.7144
1.000 0.3739 0.02700 0.01777 -0.0724 0.6977 0.7165
1.250 0.4034 0.02702 0.01778 -0.0732 0.6962 0.7187
1.500 0.4355 0.02699 0.01772 -0.0746 0.6949 0.7209
1.750 0.4203 0.02854 0.01936 -0.0695 0.6866 0.7240
2.000 0.4478 0.02871 0.01952 -0.0704 0.6843 0.7264
2.250 0.4753 0.02882 0.01965 -0.0707 0.6826 0.7282
2.500 0.5050 0.02888 0.01975 -0.0714 0.6813 0.7301
3.000 0.5091 0.03090 0.02189 -0.0656 0.6692 0.7351
3.250 0.5430 0.03084 0.02185 -0.0671 0.6677 0.7373
3.500 0.5794 0.03075 0.02179 -0.0690 0.6665 0.7397
4.000 0.5845 0.03317 0.02437 -0.0637 0.6536 0.7446
4.250 0.6167 0.03307 0.02434 -0.0645 0.6523 0.7470
4.750 0.6355 0.03535 0.02677 -0.0619 0.6391 0.7527
5.000 0.6613 0.03563 0.02711 -0.0623 0.6355 0.7555
5.500 0.6930 0.03700 0.02869 -0.0604 0.6246 0.7602
5.750 0.7230 0.03686 0.02867 -0.0608 0.6219 0.7631
6.250 0.7621 0.03781 0.02983 -0.0600 0.6096 0.7702
6.750 0.7936 0.03891 0.03120 -0.0579 0.5958 0.7759
7.000 0.8312 0.03795 0.03038 -0.0587 0.5933 0.7793
7.500 0.8859 0.03677 0.02946 -0.0580 0.5795 0.7865
8.000 0.8973 0.03849 0.03145 -0.0540 0.5531 0.7950
9.000 0.9400 0.04030 0.03371 -0.0477 0.4774 0.8148
9.250 0.9651 0.03932 0.03277 -0.0465 0.4440 0.8201
9.500 1.0140 0.03622 0.02934 -0.0461 0.3903 0.8264
9.750 1.0273 0.03658 0.02945 -0.0443 0.3439 0.8321
10.000 1.0287 0.03815 0.03077 -0.0422 0.2997 0.8388
10.250 1.0271 0.04011 0.03252 -0.0401 0.2604 0.8459
10.500 1.0242 0.04226 0.03445 -0.0382 0.2227 0.8540
10.750 1.0246 0.04418 0.03626 -0.0365 0.1905 0.8629
11.000 1.0257 0.04611 0.03805 -0.0350 0.1618 0.8735
11.500 1.0303 0.04955 0.04137 -0.0319 0.1126 0.9053
11.750 1.0310 0.05104 0.04282 -0.0300 0.0956 0.9486
12.000 1.0387 0.05286 0.04458 -0.0300 0.0816 1.0000
12.250 1.0505 0.05470 0.04643 -0.0303 0.0679 1.0000
12.500 1.0601 0.05674 0.04844 -0.0304 0.0601 1.0000
12.750 1.0708 0.05869 0.05045 -0.0306 0.0538 1.0000
13.000 1.0802 0.06077 0.05258 -0.0308 0.0482 1.0000
13.250 1.0899 0.06284 0.05474 -0.0310 0.0431 1.0000
13.500 1.0991 0.06496 0.05700 -0.0311 0.0391 1.0000
13.750 1.1065 0.06730 0.05938 -0.0313 0.0351 1.0000
14.000 1.1139 0.06970 0.06185 -0.0316 0.0321 1.0000
14.250 1.1195 0.07231 0.06451 -0.0319 0.0293 1.0000
14.500 1.1236 0.07515 0.06739 -0.0322 0.0265 1.0000
14.750 1.1312 0.07760 0.07004 -0.0326 0.0242 1.0000
15.000 1.1369 0.08032 0.07295 -0.0330 0.0220 1.0000
15.250 1.1412 0.08326 0.07605 -0.0335 0.0203 1.0000
15.500 1.1448 0.08635 0.07926 -0.0342 0.0185 1.0000
15.750 1.1477 0.08958 0.08263 -0.0350 0.0171 1.0000
16.000 1.1492 0.09304 0.08622 -0.0359 0.0158 1.0000
16.250 1.1489 0.09685 0.09016 -0.0370 0.0150 1.0000
16.500 1.1465 0.10105 0.09451 -0.0384 0.0143 1.0000
16.750 1.1433 0.10545 0.09905 -0.0399 0.0135 1.0000
17.000 1.1412 0.10978 0.10357 -0.0415 0.0127 1.0000
17.250 1.1374 0.11448 0.10846 -0.0434 0.0118 1.0000
17.500 1.1328 0.11939 0.11354 -0.0456 0.0114 1.0000
17.750 1.1272 0.12460 0.11893 -0.0481 0.0110 1.0000
18.000 1.1208 0.13008 0.12458 -0.0509 0.0106 1.0000
18.250 1.1139 0.13580 0.13045 -0.0540 0.0103 1.0000
18.500 1.1066 0.14173 0.13654 -0.0574 0.0101 1.0000
18.750 1.0983 0.14799 0.14295 -0.0611 0.0099 1.0000
19.000 1.0906 0.15426 0.14936 -0.0650 0.0097 1.0000
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Polar data table (+)
Polar graphs
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