USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 500,000 Max Cl/Cd: 69.18 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa31-il-500000-n5.txt Download as CSV file: xf-usa31-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.3076 0.09165 0.08859 -0.1751 0.9258 0.0245
-11.000 0.3094 0.08863 0.08557 -0.1767 0.9214 0.0259
-10.750 0.3152 0.08522 0.08214 -0.1795 0.9182 0.0260
-10.500 0.3132 0.08328 0.08022 -0.1780 0.9122 0.0261
-10.250 0.3159 0.08082 0.07776 -0.1782 0.9069 0.0261
-10.000 0.3256 0.07795 0.07487 -0.1800 0.9033 0.0261
-9.750 0.3217 0.07598 0.07292 -0.1782 0.8949 0.0262
-9.500 0.3360 0.07439 0.07133 -0.1783 0.8903 0.0264
-9.250 0.3419 0.07255 0.06949 -0.1779 0.8834 0.0265
-9.000 0.3563 0.07146 0.06839 -0.1777 0.8774 0.0269
-8.750 0.3678 0.06971 0.06662 -0.1784 0.8711 0.0274
-8.500 0.3749 0.06780 0.06469 -0.1787 0.8625 0.0280
-7.500 0.3561 0.05524 0.05194 -0.1795 0.8204 0.0260
-7.250 0.3604 0.05433 0.05099 -0.1781 0.8103 0.0257
-7.000 0.3591 0.05259 0.04922 -0.1770 0.7995 0.0255
-6.750 0.3580 0.04994 0.04650 -0.1774 0.7897 0.0254
-6.500 0.3561 0.04723 0.04378 -0.1773 0.7795 0.0253
-6.250 0.3471 0.04177 0.03822 -0.1794 0.7702 0.0254
-6.000 0.3016 0.02443 0.02000 -0.1875 0.7585 0.0248
-5.750 0.3113 0.02209 0.01729 -0.1860 0.7501 0.0250
-5.500 0.3229 0.02071 0.01564 -0.1837 0.7402 0.0250
-5.250 0.3355 0.01955 0.01422 -0.1813 0.7308 0.0252
-5.000 0.3481 0.01862 0.01306 -0.1786 0.7205 0.0253
-4.750 0.3595 0.01785 0.01209 -0.1754 0.7100 0.0254
-4.500 0.3700 0.01719 0.01123 -0.1720 0.6988 0.0255
-4.250 0.3819 0.01662 0.01046 -0.1688 0.6875 0.0256
-4.000 0.3958 0.01611 0.00978 -0.1660 0.6775 0.0257
-3.500 0.4262 0.01543 0.00873 -0.1608 0.6578 0.0261
-3.000 0.4594 0.01457 0.00767 -0.1562 0.6416 0.0265
-2.750 0.4770 0.01428 0.00729 -0.1542 0.6341 0.0267
-2.500 0.4958 0.01402 0.00696 -0.1523 0.6272 0.0269
-2.250 0.5149 0.01381 0.00667 -0.1505 0.6200 0.0270
-2.000 0.5336 0.01366 0.00644 -0.1486 0.6133 0.0271
-1.750 0.5542 0.01349 0.00623 -0.1470 0.6075 0.0274
-1.500 0.5743 0.01337 0.00606 -0.1454 0.6011 0.0277
-1.250 0.5939 0.01329 0.00591 -0.1437 0.5949 0.0278
-1.000 0.6145 0.01320 0.00578 -0.1422 0.5890 0.0281
-0.750 0.6349 0.01313 0.00568 -0.1406 0.5830 0.0284
-0.500 0.6545 0.01311 0.00560 -0.1389 0.5768 0.0288
-0.250 0.6753 0.01306 0.00553 -0.1374 0.5714 0.0290
0.000 0.6962 0.01303 0.00547 -0.1360 0.5652 0.0293
0.250 0.7154 0.01306 0.00545 -0.1343 0.5583 0.0296
0.500 0.7360 0.01309 0.00544 -0.1328 0.5522 0.0300
0.750 0.7563 0.01306 0.00541 -0.1313 0.5458 0.0304
1.000 0.7751 0.01311 0.00541 -0.1296 0.5390 0.0312
1.250 0.7959 0.01313 0.00543 -0.1282 0.5323 0.0318
1.500 0.8160 0.01320 0.00546 -0.1267 0.5252 0.0323
1.750 0.8349 0.01331 0.00552 -0.1250 0.5182 0.0328
2.000 0.8556 0.01339 0.00557 -0.1237 0.5112 0.0334
2.250 0.8738 0.01354 0.00568 -0.1219 0.5037 0.0340
2.500 0.8937 0.01367 0.00577 -0.1205 0.4967 0.0348
2.750 0.9126 0.01383 0.00589 -0.1188 0.4884 0.0359
3.000 0.9314 0.01401 0.00603 -0.1172 0.4820 0.0375
3.500 0.9683 0.01441 0.00640 -0.1140 0.4676 0.0485
3.750 0.9879 0.01429 0.00675 -0.1128 0.4612 0.2498
4.000 1.0072 0.01456 0.00703 -0.1113 0.4548 0.2649
4.250 1.0247 0.01489 0.00733 -0.1096 0.4488 0.2744
4.500 1.0443 0.01518 0.00762 -0.1083 0.4429 0.2845
4.750 1.0627 0.01549 0.00790 -0.1068 0.4368 0.2892
5.000 1.0795 0.01587 0.00826 -0.1051 0.4309 0.2938
5.250 1.0996 0.01614 0.00855 -0.1039 0.4260 0.2980
5.500 1.1182 0.01648 0.00887 -0.1025 0.4205 0.3029
5.750 1.1346 0.01688 0.00923 -0.1008 0.4148 0.3064
6.000 1.1532 0.01720 0.00954 -0.0994 0.4103 0.3076
6.250 1.1725 0.01749 0.00985 -0.0983 0.4051 0.3090
6.500 1.1885 0.01791 0.01025 -0.0966 0.3982 0.3102
6.750 1.2046 0.01834 0.01067 -0.0950 0.3918 0.3113
7.000 1.2228 0.01871 0.01106 -0.0937 0.3860 0.3129
7.250 1.2389 0.01917 0.01150 -0.0922 0.3801 0.3143
7.500 1.2555 0.01963 0.01196 -0.0907 0.3757 0.3157
7.750 1.2737 0.02003 0.01238 -0.0896 0.3705 0.3179
8.000 1.2895 0.02054 0.01289 -0.0881 0.3642 0.3195
8.250 1.3048 0.02109 0.01343 -0.0866 0.3597 0.3210
8.500 1.3222 0.02155 0.01391 -0.0854 0.3544 0.3226
8.750 1.3385 0.02207 0.01445 -0.0841 0.3490 0.3240
9.000 1.3526 0.02272 0.01509 -0.0826 0.3435 0.3252
9.250 1.3687 0.02328 0.01569 -0.0813 0.3386 0.3269
9.500 1.3847 0.02386 0.01630 -0.0801 0.3332 0.3281
9.750 1.3971 0.02465 0.01709 -0.0785 0.3263 0.3297
10.000 1.4122 0.02530 0.01777 -0.0773 0.3219 0.3312
10.250 1.4269 0.02600 0.01850 -0.0760 0.3159 0.3329
10.500 1.4382 0.02691 0.01940 -0.0744 0.3091 0.3347
10.750 1.4519 0.02770 0.02023 -0.0732 0.3035 0.3365
11.000 1.4656 0.02851 0.02107 -0.0720 0.2981 0.3382
11.250 1.4754 0.02958 0.02213 -0.0704 0.2918 0.3405
11.500 1.4885 0.03045 0.02304 -0.0692 0.2864 0.3421
11.750 1.4998 0.03148 0.02410 -0.0679 0.2798 0.3439
12.000 1.5075 0.03277 0.02540 -0.0663 0.2721 0.3456
12.250 1.5158 0.03407 0.02671 -0.0649 0.2628 0.3474
12.500 1.5228 0.03548 0.02813 -0.0634 0.2554 0.3488
12.750 1.5269 0.03716 0.02978 -0.0617 0.2445 0.3505
13.000 1.5335 0.03868 0.03133 -0.0604 0.2364 0.3527
13.250 1.5364 0.04054 0.03318 -0.0588 0.2277 0.3541
13.500 1.5423 0.04220 0.03486 -0.0576 0.2192 0.3560
13.750 1.5432 0.04433 0.03697 -0.0561 0.2104 0.3574
14.000 1.5482 0.04614 0.03881 -0.0550 0.2026 0.3590
14.250 1.5494 0.04834 0.04103 -0.0538 0.1957 0.3602
14.500 1.5519 0.05047 0.04318 -0.0527 0.1876 0.3623
14.750 1.5510 0.05295 0.04567 -0.0516 0.1798 0.3639
15.000 1.5541 0.05512 0.04788 -0.0507 0.1738 0.3657
15.250 1.5537 0.05763 0.05041 -0.0498 0.1681 0.3681
15.500 1.5555 0.05995 0.05278 -0.0490 0.1622 0.3707
15.750 1.5559 0.06247 0.05533 -0.0483 0.1567 0.3721
16.000 1.5535 0.06533 0.05822 -0.0476 0.1501 0.3743
16.250 1.5543 0.06791 0.06086 -0.0471 0.1446 0.3764
16.500 1.5478 0.07128 0.06423 -0.0464 0.1366 0.3780
16.750 1.5480 0.07395 0.06696 -0.0460 0.1313 0.3804
17.000 1.5414 0.07744 0.07046 -0.0456 0.1243 0.3822
17.250 1.5337 0.08110 0.07414 -0.0452 0.1155 0.3840
17.500 1.5281 0.08457 0.07762 -0.0450 0.1084 0.3858
17.750 1.5198 0.08839 0.08147 -0.0448 0.1018 0.3874
18.000 1.5125 0.09217 0.08528 -0.0448 0.0957 0.3893
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