USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 100,000 Max Cl/Cd: 40.84 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa31-il-100000-n5.txt Download as CSV file: xf-usa31-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 0.1051 0.10280 0.09750 -0.1069 0.8635 0.0764
-8.000 0.1190 0.10002 0.09471 -0.1088 0.8603 0.0784
-7.250 0.0782 0.09738 0.09220 -0.1062 0.8329 0.0831
-7.000 0.0882 0.09393 0.08875 -0.1068 0.8288 0.0838
-6.750 0.1257 0.08986 0.08466 -0.1072 0.8280 0.0863
-6.500 0.1207 0.08867 0.08350 -0.1043 0.8189 0.0880
-6.250 0.1203 0.08679 0.08163 -0.1037 0.8123 0.0910
-6.000 0.0956 0.08613 0.08098 -0.1060 0.7986 0.0944
-5.750 0.1074 0.08253 0.07737 -0.1078 0.7942 0.0951
-5.500 0.1285 0.07912 0.07393 -0.1074 0.7921 0.0961
-5.000 0.1323 0.06844 0.06303 -0.1135 0.7751 0.0645
-4.500 0.1480 0.06521 0.05981 -0.1091 0.7603 0.0607
-4.000 0.1818 0.04716 0.04098 -0.1245 0.7465 0.0505
-3.750 0.2070 0.04253 0.03598 -0.1277 0.7419 0.0501
-3.500 0.2375 0.03851 0.03151 -0.1305 0.7391 0.0495
-3.250 0.2521 0.03638 0.02900 -0.1296 0.7316 0.0491
-3.000 0.2730 0.03442 0.02663 -0.1292 0.7255 0.0488
-2.750 0.3037 0.03243 0.02421 -0.1298 0.7223 0.0486
-2.500 0.3384 0.03064 0.02203 -0.1308 0.7199 0.0486
-2.250 0.3457 0.03048 0.02168 -0.1275 0.7096 0.0487
-2.000 0.3766 0.02929 0.02021 -0.1276 0.7057 0.0489
-1.750 0.4131 0.02806 0.01870 -0.1286 0.7030 0.0496
-1.500 0.4254 0.02806 0.01852 -0.1259 0.6940 0.0504
-1.250 0.4543 0.02726 0.01768 -0.1258 0.6892 0.0513
-1.000 0.4910 0.02631 0.01667 -0.1269 0.6859 0.0527
-0.750 0.5069 0.02628 0.01660 -0.1247 0.6780 0.0532
-0.500 0.5341 0.02587 0.01611 -0.1242 0.6722 0.0538
-0.250 0.5710 0.02519 0.01533 -0.1253 0.6685 0.0548
0.000 0.5900 0.02521 0.01529 -0.1236 0.6611 0.0557
0.250 0.6160 0.02503 0.01501 -0.1230 0.6547 0.0568
0.500 0.6546 0.02443 0.01432 -0.1246 0.6505 0.0587
0.750 0.6750 0.02449 0.01434 -0.1233 0.6430 0.0617
1.000 0.7026 0.02433 0.01410 -0.1231 0.6364 0.0657
1.250 0.7441 0.02375 0.01344 -0.1253 0.6319 0.0739
1.500 0.7717 0.02358 0.01364 -0.1258 0.6243 0.1539
1.750 0.7879 0.02397 0.01430 -0.1233 0.6172 0.2425
2.000 0.8247 0.02403 0.01415 -0.1243 0.6124 0.2783
2.250 0.8312 0.02477 0.01487 -0.1206 0.6037 0.2917
2.500 0.8572 0.02502 0.01498 -0.1201 0.5974 0.3074
2.750 0.8876 0.02512 0.01499 -0.1203 0.5917 0.3202
3.000 0.8952 0.02576 0.01565 -0.1169 0.5831 0.3300
3.250 0.9226 0.02587 0.01568 -0.1167 0.5772 0.3470
3.500 0.9427 0.02618 0.01590 -0.1154 0.5706 0.3579
3.750 0.9581 0.02648 0.01621 -0.1135 0.5630 0.3618
4.000 0.9904 0.02636 0.01597 -0.1143 0.5574 0.3659
4.250 1.0040 0.02684 0.01642 -0.1122 0.5500 0.3683
4.500 1.0245 0.02715 0.01666 -0.1112 0.5431 0.3712
4.750 1.0616 0.02702 0.01642 -0.1129 0.5380 0.3747
5.000 1.0712 0.02773 0.01717 -0.1104 0.5299 0.3768
5.250 1.0972 0.02796 0.01734 -0.1105 0.5236 0.3791
5.500 1.1300 0.02801 0.01729 -0.1116 0.5183 0.3816
5.750 1.1389 0.02879 0.01812 -0.1090 0.5107 0.3833
6.000 1.1642 0.02903 0.01829 -0.1089 0.5048 0.3860
6.250 1.1908 0.02927 0.01852 -0.1091 0.4991 0.3888
6.500 1.2029 0.03000 0.01931 -0.1073 0.4921 0.3913
6.750 1.2289 0.03020 0.01947 -0.1073 0.4865 0.3942
7.000 1.2501 0.03061 0.01988 -0.1067 0.4809 0.3968
7.250 1.2601 0.03142 0.02074 -0.1045 0.4740 0.3988
7.500 1.2847 0.03167 0.02097 -0.1043 0.4688 0.4010
7.750 1.3047 0.03212 0.02144 -0.1036 0.4631 0.4034
8.000 1.3128 0.03306 0.02246 -0.1013 0.4565 0.4055
8.250 1.3356 0.03335 0.02272 -0.1009 0.4509 0.4090
8.500 1.3530 0.03392 0.02330 -0.0998 0.4454 0.4126
8.750 1.3582 0.03502 0.02451 -0.0973 0.4384 0.4150
9.000 1.3804 0.03531 0.02479 -0.0968 0.4327 0.4190
9.250 1.3924 0.03615 0.02568 -0.0952 0.4267 0.4224
9.500 1.3974 0.03735 0.02696 -0.0929 0.4199 0.4248
9.750 1.4188 0.03769 0.02729 -0.0923 0.4146 0.4285
10.000 1.4290 0.03871 0.02838 -0.0907 0.4090 0.4316
10.250 1.4313 0.04018 0.02997 -0.0883 0.4025 0.4347
10.500 1.4499 0.04070 0.03050 -0.0876 0.3973 0.4396
10.750 1.4622 0.04163 0.03150 -0.0863 0.3919 0.4450
11.000 1.4587 0.04359 0.03362 -0.0836 0.3853 0.4499
11.750 1.5175 0.04766 0.03867 -0.0868 0.3667 1.0000
12.000 1.5321 0.04842 0.03942 -0.0857 0.3615 1.0000
12.250 1.5341 0.05023 0.04130 -0.0838 0.3556 1.0000
12.500 1.5260 0.05294 0.04414 -0.0814 0.3486 1.0000
12.750 1.5430 0.05343 0.04459 -0.0806 0.3430 1.0000
13.000 1.5282 0.05693 0.04826 -0.0781 0.3357 1.0000
13.250 1.5272 0.05923 0.05064 -0.0766 0.3292 1.0000
13.500 1.5422 0.05990 0.05128 -0.0757 0.3235 1.0000
13.750 1.5177 0.06482 0.05640 -0.0736 0.3152 1.0000
14.000 1.5315 0.06557 0.05711 -0.0727 0.3089 1.0000
14.250 1.5094 0.07058 0.06229 -0.0712 0.3008 1.0000
14.500 1.5114 0.07280 0.06456 -0.0703 0.2940 1.0000
14.750 1.5071 0.07589 0.06771 -0.0694 0.2874 1.0000
15.000 1.4931 0.08030 0.07224 -0.0687 0.2797 1.0000
15.250 1.5156 0.07997 0.07185 -0.0680 0.2750 1.0000
15.500 1.4798 0.08747 0.07958 -0.0676 0.2665 1.0000
15.750 1.4880 0.08907 0.08120 -0.0671 0.2613 1.0000
16.000 1.4832 0.09251 0.08471 -0.0668 0.2553 1.0000
16.250 1.4666 0.09772 0.09005 -0.0668 0.2481 1.0000
16.500 1.4867 0.09758 0.08990 -0.0662 0.2439 1.0000
16.750 1.4557 0.10504 0.09753 -0.0669 0.2362 1.0000
17.000 1.4589 0.10743 0.09996 -0.0668 0.2306 1.0000
17.250 1.4750 0.10783 0.10035 -0.0663 0.2262 1.0000
17.500 1.4396 0.11630 0.10901 -0.0678 0.2183 1.0000
17.750 1.4566 0.11652 0.10923 -0.0674 0.2138 1.0000
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Polar data table (+)
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