USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 200,000 Max Cl/Cd: 62.3 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa31-il-200000.txt Download as CSV file: xf-usa31-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 31 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.1558 0.10043 0.09686 -0.1111 0.8882 0.0541
-9.250 0.1648 0.09695 0.09336 -0.1148 0.8863 0.0564
-9.000 0.1382 0.09629 0.09273 -0.1153 0.8769 0.0571
-8.750 0.1628 0.09159 0.08803 -0.1157 0.8744 0.0578
-8.500 0.1888 0.08782 0.08425 -0.1172 0.8728 0.0590
-8.250 0.2079 0.08433 0.08074 -0.1197 0.8711 0.0607
-8.000 0.2237 0.08062 0.07701 -0.1233 0.8697 0.0635
-7.750 0.1893 0.08032 0.07676 -0.1221 0.8569 0.0652
-7.500 0.2168 0.07540 0.07183 -0.1236 0.8560 0.0665
-7.250 0.2459 0.07169 0.06811 -0.1258 0.8551 0.0682
-7.000 0.2673 0.06792 0.06431 -0.1293 0.8541 0.0709
-6.750 0.1685 0.08203 0.07833 -0.1231 0.8549 0.0669
-6.500 0.1963 0.07888 0.07516 -0.1257 0.8537 0.0688
-5.750 0.1850 0.07148 0.06774 -0.1282 0.8258 0.0755
-5.500 0.2137 0.06876 0.06501 -0.1279 0.8247 0.0770
-5.250 0.2444 0.06578 0.06200 -0.1310 0.8232 0.0800
-5.000 0.2605 0.06124 0.05735 -0.1394 0.8168 0.0865
-4.750 0.2676 0.05978 0.05591 -0.1360 0.8090 0.0875
-4.500 0.3023 0.05726 0.05335 -0.1386 0.8073 0.0910
-4.250 0.3439 0.05262 0.04858 -0.1481 0.8051 0.0996
-4.000 0.3684 0.05103 0.04696 -0.1482 0.8003 0.1031
-3.000 0.4592 0.04225 0.03788 -0.1541 0.7740 0.1299
-2.750 0.5075 0.03914 0.03458 -0.1609 0.7707 0.1433
-2.500 0.4831 0.02343 0.01643 -0.1569 0.7597 0.0652
-2.250 0.5214 0.02158 0.01437 -0.1588 0.7555 0.0636
-2.000 0.5713 0.02015 0.01264 -0.1627 0.7524 0.0621
-1.750 0.5717 0.01992 0.01232 -0.1570 0.7423 0.0623
-1.500 0.6131 0.01910 0.01131 -0.1593 0.7374 0.0633
-1.250 0.6455 0.01849 0.01059 -0.1598 0.7313 0.0635
-1.000 0.6606 0.01815 0.01020 -0.1570 0.7228 0.0635
-0.750 0.7057 0.01752 0.00948 -0.1601 0.7180 0.0639
-0.500 0.7136 0.01742 0.00937 -0.1558 0.7089 0.0643
-0.250 0.7479 0.01707 0.00896 -0.1568 0.7025 0.0653
0.000 0.7701 0.01688 0.00877 -0.1554 0.6950 0.0667
0.250 0.7926 0.01676 0.00861 -0.1541 0.6872 0.0686
0.500 0.8337 0.01656 0.00828 -0.1566 0.6811 0.0744
0.750 0.8427 0.01652 0.00826 -0.1526 0.6720 0.0805
1.000 0.8852 0.01609 0.00828 -0.1556 0.6656 0.2286
1.250 0.8928 0.01652 0.00870 -0.1512 0.6567 0.2687
1.500 0.9223 0.01710 0.00917 -0.1512 0.6494 0.2931
1.750 0.9381 0.01758 0.00957 -0.1486 0.6413 0.3074
2.000 0.9589 0.01804 0.01003 -0.1469 0.6332 0.3208
2.250 0.9845 0.01834 0.01029 -0.1465 0.6258 0.3325
2.500 0.9989 0.01858 0.01043 -0.1437 0.6176 0.3404
2.750 1.0386 0.01879 0.01051 -0.1461 0.6109 0.3557
3.000 1.0387 0.01889 0.01072 -0.1407 0.6022 0.3618
3.250 1.0673 0.01896 0.01070 -0.1409 0.5951 0.3768
3.500 1.0812 0.01925 0.01093 -0.1382 0.5874 0.3849
3.750 1.0999 0.01925 0.01092 -0.1366 0.5799 0.3896
4.000 1.1296 0.01932 0.01089 -0.1371 0.5731 0.3940
4.250 1.1369 0.01959 0.01117 -0.1332 0.5651 0.3961
4.500 1.1651 0.01972 0.01116 -0.1334 0.5587 0.3994
4.750 1.1788 0.01994 0.01140 -0.1309 0.5515 0.4009
5.000 1.1957 0.02008 0.01153 -0.1289 0.5444 0.4024
5.250 1.2285 0.02013 0.01147 -0.1301 0.5383 0.4046
5.500 1.2331 0.02047 0.01190 -0.1259 0.5311 0.4058
5.750 1.2545 0.02062 0.01201 -0.1249 0.5247 0.4086
6.000 1.2780 0.02085 0.01218 -0.1243 0.5186 0.4115
6.250 1.2875 0.02119 0.01256 -0.1212 0.5116 0.4130
6.500 1.3128 0.02137 0.01267 -0.1210 0.5059 0.4147
6.750 1.3298 0.02164 0.01298 -0.1193 0.4994 0.4165
7.000 1.3433 0.02194 0.01332 -0.1171 0.4927 0.4185
7.250 1.3737 0.02205 0.01334 -0.1178 0.4866 0.4212
7.500 1.3796 0.02252 0.01391 -0.1143 0.4800 0.4230
7.750 1.3954 0.02283 0.01422 -0.1125 0.4733 0.4254
8.000 1.4251 0.02308 0.01439 -0.1133 0.4673 0.4288
8.250 1.4366 0.02363 0.01508 -0.1112 0.4607 0.4319
8.500 1.4616 0.02395 0.01541 -0.1114 0.4546 0.4355
8.750 1.4880 0.02430 0.01574 -0.1117 0.4489 0.4391
9.000 1.4967 0.02491 0.01645 -0.1090 0.4428 0.4418
9.250 1.5165 0.02529 0.01683 -0.1082 0.4371 0.4453
9.500 1.5408 0.02567 0.01721 -0.1082 0.4314 0.4496
9.750 1.5467 0.02638 0.01803 -0.1052 0.4252 0.4529
10.000 1.5653 0.02681 0.01845 -0.1043 0.4194 0.4578
10.250 1.5816 0.02736 0.01902 -0.1030 0.4130 0.4635
10.500 1.5875 0.02814 0.01993 -0.1003 0.4067 0.4708
10.750 1.6080 0.02853 0.02032 -0.0998 0.4005 0.4880
11.000 1.6752 0.02985 0.02249 -0.1112 0.3901 1.0000
11.250 1.6880 0.03049 0.02310 -0.1094 0.3841 1.0000
11.500 1.6989 0.03130 0.02392 -0.1075 0.3782 1.0000
11.750 1.7001 0.03244 0.02517 -0.1044 0.3718 1.0000
12.000 1.7139 0.03309 0.02578 -0.1029 0.3660 1.0000
12.250 1.7172 0.03427 0.02706 -0.1003 0.3597 1.0000
12.500 1.7188 0.03554 0.02841 -0.0975 0.3533 1.0000
12.750 1.7365 0.03605 0.02880 -0.0966 0.3469 1.0000
13.000 1.7266 0.03805 0.03100 -0.0929 0.3400 1.0000
13.250 1.7311 0.03930 0.03226 -0.0908 0.3331 1.0000
13.500 1.7334 0.04081 0.03382 -0.0886 0.3263 1.0000
13.750 1.7306 0.04269 0.03578 -0.0861 0.3188 1.0000
14.000 1.7350 0.04413 0.03719 -0.0842 0.3116 1.0000
14.250 1.7293 0.04646 0.03965 -0.0819 0.3040 1.0000
14.500 1.7359 0.04782 0.04092 -0.0804 0.2969 1.0000
14.750 1.7285 0.05055 0.04383 -0.0783 0.2894 1.0000
15.000 1.7313 0.05233 0.04557 -0.0768 0.2824 1.0000
15.250 1.7257 0.05507 0.04844 -0.0751 0.2749 1.0000
15.500 1.7250 0.05735 0.05072 -0.0737 0.2677 1.0000
15.750 1.7237 0.05981 0.05324 -0.0725 0.2611 1.0000
16.000 1.7195 0.06262 0.05612 -0.0712 0.2539 1.0000
16.250 1.7195 0.06496 0.05846 -0.0702 0.2474 1.0000
16.500 1.7122 0.06828 0.06190 -0.0692 0.2401 1.0000
16.750 1.7123 0.07066 0.06420 -0.0683 0.2335 1.0000
17.000 1.7032 0.07438 0.06809 -0.0675 0.2264 1.0000
17.250 1.7008 0.07715 0.07083 -0.0668 0.2201 1.0000
17.500 1.6937 0.08068 0.07449 -0.0663 0.2136 1.0000
17.750 1.6890 0.08389 0.07774 -0.0658 0.2074 1.0000
18.000 1.6850 0.08701 0.08087 -0.0654 0.2015 1.0000
18.250 1.6771 0.09080 0.08479 -0.0652 0.1953 1.0000
18.500 1.6745 0.09372 0.08764 -0.0649 0.1894 1.0000
18.750 1.6651 0.09785 0.09194 -0.0650 0.1836 1.0000
19.000 1.6592 0.10138 0.09550 -0.0651 0.1779 1.0000
19.250 1.6545 0.10475 0.09888 -0.0652 0.1724 1.0000
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