FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-K-170/22 (fx73k170-il) Reynolds number: 100,000 Max Cl/Cd: 26.3 at α=11° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73k170-il-100000-n5.txt Download as CSV file: xf-fx73k170-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-K-170/22
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.0698 0.10032 0.09449 -0.1295 0.8754 0.0261
-11.750 -0.0690 0.09578 0.08998 -0.1319 0.8723 0.0256
-11.500 -0.0695 0.09086 0.08508 -0.1347 0.8693 0.0252
-11.000 -0.1290 0.06730 0.06141 -0.1497 0.8633 0.0223
-10.750 -0.1423 0.06295 0.05702 -0.1520 0.8591 0.0221
-10.500 -0.1665 0.05803 0.05195 -0.1546 0.8545 0.0221
-10.250 -0.1812 0.05447 0.04824 -0.1558 0.8505 0.0220
-10.000 -0.1919 0.05217 0.04585 -0.1553 0.8460 0.0218
-9.750 -0.2123 0.04962 0.04314 -0.1538 0.8407 0.0218
-9.500 -0.2268 0.04770 0.04105 -0.1517 0.8364 0.0218
-9.250 -0.2371 0.04590 0.03904 -0.1493 0.8322 0.0217
-9.000 -0.2467 0.04408 0.03698 -0.1464 0.8270 0.0218
-8.750 -0.2482 0.04202 0.03460 -0.1443 0.8232 0.0218
-8.500 -0.2424 0.03999 0.03220 -0.1429 0.8203 0.0220
-8.250 -0.2370 0.03839 0.03032 -0.1407 0.8164 0.0221
-8.000 -0.2308 0.03689 0.02858 -0.1385 0.8118 0.0226
-7.750 -0.2167 0.03564 0.02721 -0.1374 0.8085 0.0233
-7.500 -0.1993 0.03472 0.02617 -0.1367 0.8060 0.0250
-7.250 -0.1785 0.03337 0.02458 -0.1362 0.8040 0.0261
-7.000 -0.1708 0.03271 0.02374 -0.1333 0.7988 0.0272
-6.750 -0.1542 0.03169 0.02254 -0.1317 0.7950 0.0280
-6.500 -0.1342 0.03053 0.02129 -0.1307 0.7922 0.0291
-6.250 -0.1131 0.02955 0.02028 -0.1300 0.7901 0.0305
-6.000 -0.0945 0.02885 0.01953 -0.1288 0.7876 0.0324
-5.750 -0.0903 0.02879 0.01945 -0.1254 0.7816 0.0339
-5.500 -0.0738 0.02818 0.01878 -0.1240 0.7782 0.0379
-5.250 -0.0527 0.02753 0.01806 -0.1234 0.7757 0.0429
-5.000 -0.0298 0.02676 0.01724 -0.1230 0.7738 0.0503
-4.750 -0.0278 0.02687 0.01737 -0.1194 0.7676 0.0585
-4.500 -0.0128 0.02639 0.01696 -0.1179 0.7637 0.0767
-4.250 0.0071 0.02548 0.01635 -0.1174 0.7611 0.1330
-4.000 0.0253 0.02390 0.01570 -0.1174 0.7590 0.3195
-3.750 0.0250 0.02409 0.01656 -0.1131 0.7528 0.4462
-3.500 0.0390 0.02465 0.01732 -0.1103 0.7486 0.5263
-3.250 0.0639 0.02507 0.01760 -0.1093 0.7462 0.5731
-3.000 0.0907 0.02549 0.01788 -0.1085 0.7444 0.6041
-2.750 0.0985 0.02632 0.01866 -0.1051 0.7389 0.6234
-2.500 0.1072 0.02707 0.01935 -0.1018 0.7336 0.6390
-2.250 0.1311 0.02734 0.01951 -0.1007 0.7312 0.6535
-2.000 0.1590 0.02739 0.01939 -0.1006 0.7295 0.6644
-1.750 0.1548 0.02823 0.02022 -0.0959 0.7220 0.6714
-1.500 0.1723 0.02851 0.02038 -0.0945 0.7179 0.6793
-1.250 0.1987 0.02854 0.02030 -0.0942 0.7159 0.6859
-1.000 0.2293 0.02845 0.02004 -0.0949 0.7143 0.6933
-0.750 0.2177 0.02971 0.02133 -0.0895 0.7053 0.6977
-0.500 0.2414 0.02984 0.02136 -0.0891 0.7024 0.7035
-0.250 0.2707 0.02977 0.02115 -0.0895 0.7005 0.7093
0.000 0.2999 0.02968 0.02099 -0.0898 0.6991 0.7133
0.500 0.3187 0.03119 0.02238 -0.0857 0.6872 0.7237
0.750 0.3466 0.03116 0.02230 -0.0858 0.6855 0.7272
1.000 0.3769 0.03106 0.02214 -0.0863 0.6841 0.7311
1.500 0.3977 0.03260 0.02360 -0.0827 0.6721 0.7400
1.750 0.4269 0.03251 0.02349 -0.0829 0.6704 0.7433
2.000 0.4578 0.03238 0.02332 -0.0835 0.6691 0.7471
2.250 0.4509 0.03403 0.02497 -0.0799 0.6588 0.7517
2.500 0.4801 0.03403 0.02493 -0.0803 0.6567 0.7558
2.750 0.5108 0.03388 0.02478 -0.0808 0.6552 0.7592
3.250 0.5364 0.03549 0.02640 -0.0782 0.6429 0.7679
3.500 0.5673 0.03541 0.02631 -0.0789 0.6411 0.7720
3.750 0.6002 0.03518 0.02609 -0.0797 0.6398 0.7757
4.250 0.6272 0.03695 0.02791 -0.0775 0.6269 0.7853
4.500 0.6596 0.03677 0.02776 -0.0783 0.6254 0.7895
5.000 0.6895 0.03846 0.02954 -0.0767 0.6124 0.7998
5.250 0.7223 0.03820 0.02936 -0.0775 0.6107 0.8050
5.500 0.7568 0.03781 0.02903 -0.0784 0.6095 0.8109
6.000 0.7881 0.03954 0.03093 -0.0772 0.5959 0.8234
6.250 0.8223 0.03915 0.03063 -0.0781 0.5946 0.8314
6.500 0.8218 0.04120 0.03280 -0.0763 0.5827 0.8402
6.750 0.8563 0.04076 0.03248 -0.0773 0.5809 0.8506
7.250 0.8960 0.04220 0.03424 -0.0775 0.5672 0.8830
7.500 0.9364 0.04128 0.03354 -0.0796 0.5654 0.9838
8.000 0.9638 0.04270 0.03506 -0.0771 0.5511 1.0000
8.250 0.9997 0.04190 0.03434 -0.0778 0.5495 1.0000
8.500 1.0009 0.04389 0.03640 -0.0763 0.5369 1.0000
8.750 1.0367 0.04295 0.03556 -0.0768 0.5349 1.0000
9.000 1.0392 0.04483 0.03753 -0.0753 0.5224 1.0000
9.250 1.0758 0.04370 0.03650 -0.0758 0.5200 1.0000
9.500 1.0799 0.04540 0.03829 -0.0744 0.5076 1.0000
9.750 1.1188 0.04393 0.03696 -0.0748 0.5046 1.0000
10.000 1.1240 0.04549 0.03861 -0.0734 0.4917 1.0000
10.250 1.1353 0.04653 0.03975 -0.0723 0.4800 1.0000
10.500 1.1650 0.04575 0.03908 -0.0720 0.4718 1.0000
10.750 1.1889 0.04544 0.03888 -0.0714 0.4598 1.0000
11.000 1.2057 0.04585 0.03937 -0.0705 0.4448 1.0000
11.250 1.2193 0.04656 0.04012 -0.0694 0.4264 1.0000
11.500 1.2323 0.04731 0.04089 -0.0682 0.4046 1.0000
11.750 1.2471 0.04781 0.04131 -0.0670 0.3776 1.0000
12.000 1.2570 0.04886 0.04227 -0.0657 0.3480 1.0000
12.250 1.2614 0.05052 0.04378 -0.0642 0.3156 1.0000
12.500 1.2642 0.05249 0.04564 -0.0628 0.2867 1.0000
12.750 1.2633 0.05492 0.04791 -0.0614 0.2569 1.0000
13.000 1.2612 0.05758 0.05045 -0.0602 0.2295 1.0000
13.250 1.2581 0.06046 0.05321 -0.0591 0.2042 1.0000
13.500 1.2533 0.06365 0.05629 -0.0581 0.1774 1.0000
13.750 1.2490 0.06689 0.05943 -0.0573 0.1535 1.0000
14.000 1.2436 0.07031 0.06274 -0.0566 0.1326 1.0000
14.250 1.2398 0.07367 0.06606 -0.0561 0.1126 1.0000
14.500 1.2355 0.07716 0.06949 -0.0557 0.0963 1.0000
14.750 1.2313 0.08072 0.07300 -0.0554 0.0829 1.0000
15.000 1.2287 0.08413 0.07641 -0.0552 0.0730 1.0000
15.250 1.2256 0.08766 0.07995 -0.0551 0.0656 1.0000
15.500 1.2240 0.09108 0.08341 -0.0551 0.0588 1.0000
15.750 1.2224 0.09451 0.08688 -0.0552 0.0540 1.0000
16.000 1.2220 0.09784 0.09031 -0.0554 0.0493 1.0000
16.250 1.2186 0.10157 0.09401 -0.0558 0.0458 1.0000
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