USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.2 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa31-il-1000000.txt Download as CSV file: xf-usa31-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 0.3003 0.09902 0.09694 -0.1712 0.9491 0.0209
-13.250 0.3036 0.09548 0.09339 -0.1736 0.9473 0.0210
-13.000 0.3078 0.09183 0.08972 -0.1760 0.9456 0.0211
-12.750 0.3225 0.08876 0.08664 -0.1773 0.9440 0.0212
-12.500 0.3278 0.08700 0.08490 -0.1761 0.9410 0.0213
-12.250 0.3358 0.08518 0.08308 -0.1757 0.9379 0.0214
-12.000 0.3460 0.08303 0.08093 -0.1764 0.9350 0.0216
-11.750 0.3569 0.08067 0.07855 -0.1775 0.9328 0.0219
-11.500 0.3677 0.07814 0.07601 -0.1788 0.9305 0.0222
-11.250 0.3751 0.07586 0.07373 -0.1792 0.9276 0.0227
-11.000 0.3768 0.07388 0.07176 -0.1782 0.9229 0.0228
-10.750 0.3828 0.07137 0.06925 -0.1785 0.9192 0.0235
-10.500 0.3786 0.06722 0.06507 -0.1805 0.9153 0.0245
-10.000 0.3736 0.06092 0.05877 -0.1799 0.9041 0.0248
-9.750 0.3851 0.05880 0.05662 -0.1800 0.8996 0.0250
-9.500 0.3895 0.05711 0.05495 -0.1789 0.8923 0.0251
-9.250 0.3983 0.05523 0.05303 -0.1788 0.8852 0.0252
-9.000 0.4042 0.05347 0.05126 -0.1781 0.8761 0.0254
-8.750 0.4113 0.05145 0.04919 -0.1781 0.8675 0.0256
-8.500 0.4161 0.04968 0.04739 -0.1775 0.8572 0.0259
-8.250 0.4199 0.04760 0.04527 -0.1772 0.8483 0.0261
-8.000 0.4231 0.04560 0.04323 -0.1768 0.8387 0.0266
-7.750 0.4238 0.04345 0.04106 -0.1763 0.8297 0.0271
-7.500 0.4211 0.04090 0.03845 -0.1761 0.8208 0.0279
-7.250 0.3889 0.03567 0.03323 -0.1762 0.8102 0.0286
-7.000 0.3558 0.03031 0.02782 -0.1758 0.8009 0.0289
-6.750 0.3628 0.02920 0.02671 -0.1749 0.7927 0.0290
-6.500 0.3675 0.02732 0.02478 -0.1749 0.7848 0.0292
-6.250 0.3820 0.03787 0.03521 -0.1910 0.7957 0.0294
-6.000 0.3927 0.03602 0.03328 -0.1911 0.7875 0.0297
-5.750 0.3776 0.02558 0.02245 -0.1962 0.7782 0.0305
-5.500 0.3874 0.02252 0.01905 -0.1959 0.7697 0.0315
-5.250 0.4013 0.02185 0.01785 -0.1941 0.7612 0.0330
-5.000 0.4013 0.01875 0.01439 -0.1903 0.7519 0.0337
-4.750 0.4172 0.01776 0.01339 -0.1883 0.7429 0.0340
-4.500 0.4313 0.01704 0.01259 -0.1857 0.7329 0.0343
-4.250 0.4449 0.01641 0.01188 -0.1830 0.7216 0.0347
-4.000 0.4545 0.01586 0.01120 -0.1793 0.7097 0.0352
-3.750 0.4617 0.01539 0.01060 -0.1751 0.6978 0.0357
-3.500 0.4720 0.01501 0.01005 -0.1714 0.6858 0.0366
-3.250 0.4818 0.01469 0.00938 -0.1675 0.6751 0.0387
-3.000 0.4927 0.01395 0.00860 -0.1642 0.6643 0.0392
-2.750 0.5094 0.01348 0.00809 -0.1619 0.6553 0.0398
-2.500 0.5240 0.01322 0.00775 -0.1592 0.6464 0.0407
-2.250 0.5414 0.01196 0.00617 -0.1561 0.6394 0.0314
-2.000 0.5583 0.01159 0.00570 -0.1537 0.6319 0.0309
-1.750 0.5777 0.01135 0.00539 -0.1518 0.6254 0.0309
-1.500 0.5972 0.01118 0.00516 -0.1500 0.6187 0.0309
-1.250 0.6150 0.01112 0.00502 -0.1478 0.6116 0.0312
-1.000 0.6364 0.01095 0.00482 -0.1464 0.6061 0.0312
-0.750 0.6569 0.01086 0.00470 -0.1448 0.6001 0.0314
-0.500 0.6752 0.01082 0.00460 -0.1427 0.5936 0.0315
-0.250 0.6967 0.01074 0.00450 -0.1414 0.5881 0.0318
0.000 0.7169 0.01069 0.00442 -0.1397 0.5818 0.0319
0.250 0.7357 0.01073 0.00440 -0.1378 0.5756 0.0321
0.500 0.7582 0.01069 0.00436 -0.1367 0.5704 0.0326
0.750 0.7795 0.01073 0.00437 -0.1353 0.5640 0.0331
1.250 0.8195 0.01066 0.00423 -0.1321 0.5511 0.0341
1.500 0.8394 0.01069 0.00423 -0.1305 0.5443 0.0351
1.750 0.8587 0.01078 0.00428 -0.1288 0.5375 0.0358
2.000 0.8803 0.01082 0.00431 -0.1276 0.5301 0.0366
2.250 0.8990 0.01096 0.00439 -0.1258 0.5225 0.0374
2.500 0.9206 0.01104 0.00446 -0.1246 0.5156 0.0381
2.750 0.9398 0.01117 0.00455 -0.1230 0.5077 0.0396
3.000 0.9586 0.01132 0.00467 -0.1213 0.5002 0.0428
3.250 0.9773 0.01121 0.00480 -0.1197 0.4920 0.1596
3.500 0.9949 0.01131 0.00511 -0.1179 0.4845 0.2591
3.750 1.0161 0.01152 0.00532 -0.1167 0.4773 0.2747
4.000 1.0335 0.01185 0.00561 -0.1149 0.4690 0.2841
4.250 1.0543 0.01207 0.00582 -0.1137 0.4625 0.2886
4.500 1.0724 0.01234 0.00606 -0.1120 0.4554 0.2917
4.750 1.0910 0.01262 0.00633 -0.1105 0.4491 0.2963
5.000 1.1112 0.01290 0.00660 -0.1093 0.4423 0.3015
5.250 1.1285 0.01325 0.00691 -0.1075 0.4353 0.3049
5.500 1.1480 0.01352 0.00717 -0.1062 0.4290 0.3092
5.750 1.1658 0.01382 0.00745 -0.1046 0.4219 0.3113
6.000 1.1825 0.01417 0.00777 -0.1029 0.4152 0.3127
6.250 1.2037 0.01438 0.00800 -0.1020 0.4107 0.3141
6.500 1.2224 0.01467 0.00828 -0.1006 0.4048 0.3154
6.750 1.2379 0.01509 0.00867 -0.0988 0.3989 0.3168
7.000 1.2585 0.01534 0.00893 -0.0978 0.3938 0.3185
7.250 1.2778 0.01563 0.00924 -0.0967 0.3894 0.3200
7.500 1.2938 0.01607 0.00964 -0.0950 0.3831 0.3214
7.750 1.3129 0.01640 0.00998 -0.0939 0.3784 0.3226
8.000 1.3318 0.01673 0.01032 -0.0928 0.3739 0.3236
8.250 1.3489 0.01714 0.01072 -0.0914 0.3687 0.3252
8.500 1.3654 0.01760 0.01117 -0.0900 0.3635 0.3271
8.750 1.3855 0.01791 0.01153 -0.0891 0.3594 0.3287
9.000 1.4025 0.01836 0.01200 -0.0879 0.3540 0.3304
9.250 1.4173 0.01893 0.01255 -0.0863 0.3484 0.3326
9.500 1.4360 0.01934 0.01298 -0.0854 0.3439 0.3346
9.750 1.4528 0.01984 0.01350 -0.0841 0.3380 0.3363
10.000 1.4676 0.02044 0.01410 -0.0827 0.3331 0.3378
10.250 1.4840 0.02099 0.01466 -0.0815 0.3281 0.3393
10.500 1.5011 0.02151 0.01520 -0.0805 0.3229 0.3406
10.750 1.5123 0.02238 0.01605 -0.0788 0.3144 0.3429
11.000 1.5287 0.02298 0.01666 -0.0778 0.3063 0.3449
11.250 1.5429 0.02371 0.01741 -0.0765 0.3015 0.3467
11.500 1.5545 0.02460 0.01829 -0.0750 0.2917 0.3483
11.750 1.5665 0.02548 0.01917 -0.0736 0.2843 0.3506
12.000 1.5784 0.02641 0.02010 -0.0722 0.2771 0.3525
12.250 1.5906 0.02733 0.02103 -0.0709 0.2700 0.3541
12.500 1.5998 0.02846 0.02213 -0.0693 0.2612 0.3557
12.750 1.6077 0.02973 0.02338 -0.0677 0.2518 0.3577
13.000 1.6179 0.03088 0.02455 -0.0665 0.2430 0.3602
13.250 1.6244 0.03231 0.02597 -0.0649 0.2350 0.3621
13.500 1.6343 0.03353 0.02720 -0.0637 0.2273 0.3640
13.750 1.6376 0.03525 0.02889 -0.0620 0.2178 0.3666
14.000 1.6430 0.03685 0.03049 -0.0606 0.2084 0.3685
14.250 1.6477 0.03853 0.03216 -0.0592 0.2006 0.3701
14.500 1.6522 0.04031 0.03395 -0.0579 0.1931 0.3725
14.750 1.6572 0.04211 0.03576 -0.0568 0.1863 0.3747
15.000 1.6589 0.04421 0.03786 -0.0555 0.1780 0.3767
15.250 1.6617 0.04624 0.03991 -0.0544 0.1715 0.3786
15.500 1.6633 0.04838 0.04206 -0.0533 0.1643 0.3815
15.750 1.6649 0.05059 0.04429 -0.0522 0.1591 0.3831
16.000 1.6646 0.05298 0.04669 -0.0511 0.1517 0.3853
16.250 1.6629 0.05559 0.04931 -0.0502 0.1439 0.3880
16.500 1.6615 0.05821 0.05194 -0.0493 0.1372 0.3906
16.750 1.6588 0.06097 0.05473 -0.0484 0.1309 0.3940
17.000 1.6488 0.06447 0.05821 -0.0473 0.1202 0.3961
17.250 1.6417 0.06774 0.06147 -0.0464 0.1110 0.3983
17.500 1.6269 0.07185 0.06555 -0.0454 0.1001 0.3996
17.750 1.6205 0.07522 0.06895 -0.0448 0.0951 0.4030
18.000 1.6101 0.07906 0.07281 -0.0443 0.0889 0.4056
18.250 1.6042 0.08244 0.07623 -0.0440 0.0842 0.4101
18.500 1.5947 0.08628 0.08010 -0.0436 0.0796 0.4130
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