USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 50,000 Max Cl/Cd: 38.87 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa5-il-50000.txt Download as CSV file: xf-usa5-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: USA 5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3453 0.11013 0.10340 -0.0216 1.0000 0.1148
-8.250 -0.3508 0.10920 0.10259 -0.0226 1.0000 0.1177
-8.000 -0.3616 0.10903 0.10257 -0.0233 1.0000 0.1187
-7.750 -0.3454 0.10275 0.09625 -0.0218 1.0000 0.1228
-7.500 -0.3438 0.10012 0.09370 -0.0210 1.0000 0.1271
-7.250 -0.3510 0.09882 0.09253 -0.0208 1.0000 0.1304
-7.000 -0.3601 0.09866 0.09250 -0.0234 1.0000 0.1324
-6.750 -0.3523 0.09373 0.08764 -0.0212 1.0000 0.1353
-6.500 -0.3478 0.09048 0.08445 -0.0199 1.0000 0.1403
-6.250 -0.3500 0.08905 0.08310 -0.0214 1.0000 0.1451
-6.000 -0.3504 0.08716 0.08128 -0.0235 1.0000 0.1475
-5.750 -0.3439 0.08279 0.07697 -0.0199 1.0000 0.1525
-5.500 -0.3414 0.08115 0.07535 -0.0217 1.0000 0.1593
-5.000 -0.3321 0.07494 0.06924 -0.0200 1.0000 0.1706
-4.750 -0.3258 0.07229 0.06659 -0.0211 1.0000 0.1771
-4.500 -0.3147 0.07092 0.06512 -0.0240 1.0000 0.1885
-4.250 -0.3115 0.06650 0.06084 -0.0198 1.0000 0.1944
-4.000 -0.3023 0.06371 0.05803 -0.0200 1.0000 0.2064
-3.750 -0.2939 0.06093 0.05525 -0.0192 1.0000 0.2226
-3.500 -0.2848 0.05831 0.05261 -0.0189 1.0000 0.2463
-3.250 -0.2778 0.05556 0.04985 -0.0172 1.0000 0.2746
-3.000 -0.2716 0.05289 0.04722 -0.0147 1.0000 0.3053
-2.750 -0.2678 0.05025 0.04466 -0.0115 1.0000 0.3481
-2.500 -0.2679 0.04754 0.04207 -0.0068 1.0000 0.4025
-2.250 -0.2666 0.04484 0.03945 -0.0023 1.0000 0.4557
-2.000 -0.2626 0.04207 0.03676 0.0020 1.0000 0.4996
-1.750 -0.2515 0.03956 0.03425 0.0042 1.0000 0.5358
-1.500 -0.2370 0.03707 0.03174 0.0055 1.0000 0.5674
-1.250 -0.2009 0.03477 0.02920 0.0008 1.0000 0.5582
-1.000 -0.0493 0.03413 0.02540 -0.0271 1.0000 0.1734
-0.750 -0.0294 0.03254 0.02361 -0.0264 1.0000 0.1801
-0.500 -0.0066 0.03120 0.02188 -0.0257 1.0000 0.1815
-0.250 0.0171 0.03006 0.02030 -0.0252 1.0000 0.1838
0.000 0.0372 0.02945 0.01934 -0.0245 1.0000 0.2018
0.250 0.0861 0.02841 0.01793 -0.0290 0.9909 0.2216
0.500 0.1626 0.02759 0.01680 -0.0384 0.9741 0.2815
0.750 0.2341 0.02706 0.01643 -0.0471 0.9559 0.3486
1.000 0.3261 0.02520 0.01587 -0.0596 0.9377 1.0000
1.250 0.3897 0.02567 0.01574 -0.0661 0.9141 1.0000
1.500 0.4447 0.02587 0.01566 -0.0710 0.8882 1.0000
1.750 0.4984 0.02588 0.01551 -0.0755 0.8629 1.0000
2.000 0.5542 0.02564 0.01518 -0.0799 0.8392 1.0000
2.250 0.6076 0.02523 0.01472 -0.0834 0.8179 1.0000
2.500 0.6457 0.02516 0.01465 -0.0844 0.7940 1.0000
2.750 0.6901 0.02482 0.01427 -0.0860 0.7746 1.0000
3.000 0.7184 0.02507 0.01452 -0.0854 0.7522 1.0000
3.250 0.7545 0.02497 0.01440 -0.0857 0.7341 1.0000
3.500 0.7789 0.02539 0.01489 -0.0845 0.7133 1.0000
3.750 0.8083 0.02552 0.01502 -0.0838 0.6948 1.0000
4.000 0.8368 0.02566 0.01516 -0.0828 0.6764 1.0000
4.250 0.8592 0.02610 0.01564 -0.0812 0.6563 1.0000
4.500 0.8861 0.02631 0.01587 -0.0799 0.6381 1.0000
4.750 0.9116 0.02671 0.01638 -0.0787 0.6210 1.0000
5.000 0.9327 0.02749 0.01729 -0.0774 0.6048 1.0000
5.250 0.9546 0.02828 0.01822 -0.0761 0.5891 1.0000
5.500 0.9765 0.02906 0.01914 -0.0748 0.5730 1.0000
5.750 0.9992 0.02975 0.01999 -0.0734 0.5564 1.0000
6.000 1.0237 0.03035 0.02080 -0.0721 0.5395 1.0000
6.250 1.0436 0.03075 0.02134 -0.0698 0.5159 1.0000
6.500 1.0694 0.02967 0.02008 -0.0667 0.4818 1.0000
6.750 1.0902 0.02962 0.02005 -0.0642 0.4544 1.0000
7.000 1.1085 0.02978 0.02032 -0.0617 0.4278 1.0000
7.250 1.1254 0.03013 0.02093 -0.0591 0.4031 1.0000
7.500 1.1398 0.02984 0.02068 -0.0557 0.3723 1.0000
7.750 1.1456 0.02955 0.02053 -0.0513 0.3361 1.0000
8.000 1.1448 0.02945 0.02049 -0.0461 0.2880 1.0000
8.250 1.1412 0.03022 0.02101 -0.0411 0.2000 1.0000
8.500 1.1344 0.03299 0.02301 -0.0367 0.1283 1.0000
8.750 1.1336 0.03556 0.02522 -0.0333 0.0997 1.0000
9.000 1.1327 0.03787 0.02744 -0.0298 0.0897 1.0000
9.250 1.1318 0.04012 0.02970 -0.0264 0.0839 1.0000
9.500 1.1325 0.04238 0.03201 -0.0234 0.0789 1.0000
9.750 1.1353 0.04485 0.03446 -0.0208 0.0742 1.0000
10.000 1.1460 0.04709 0.03692 -0.0186 0.0692 1.0000
10.250 1.1693 0.04950 0.03951 -0.0171 0.0660 1.0000
10.500 1.2260 0.05416 0.04432 -0.0190 0.0637 1.0000
10.750 1.2473 0.05831 0.04887 -0.0182 0.0637 1.0000
11.000 1.2523 0.06201 0.05302 -0.0160 0.0640 1.0000
11.250 1.2461 0.06530 0.05674 -0.0130 0.0646 1.0000
11.500 1.2330 0.06871 0.06054 -0.0101 0.0653 1.0000
11.750 1.2135 0.07262 0.06482 -0.0079 0.0660 1.0000
12.000 1.1895 0.07690 0.06941 -0.0070 0.0666 1.0000
12.250 1.1621 0.08218 0.07497 -0.0077 0.0672 1.0000
12.500 1.1339 0.08825 0.08128 -0.0100 0.0679 1.0000
12.750 1.1025 0.09577 0.08898 -0.0143 0.0687 1.0000
13.000 1.0691 0.10492 0.09826 -0.0203 0.0697 1.0000
13.250 1.0373 0.11549 0.10889 -0.0273 0.0712 1.0000
13.500 1.0131 0.12590 0.11928 -0.0335 0.0729 1.0000
13.750 1.0010 0.13409 0.12744 -0.0374 0.0743 1.0000
14.000 0.9979 0.14043 0.13376 -0.0394 0.0754 1.0000
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