USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 200,000 Max Cl/Cd: 54.84 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa31-il-200000-n5.txt Download as CSV file: xf-usa31-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2092 0.09588 0.09168 -0.1388 0.8966 0.0417
-9.500 0.2178 0.09333 0.08912 -0.1404 0.8927 0.0434
-9.250 0.2165 0.08971 0.08549 -0.1469 0.8894 0.0446
-9.000 0.2177 0.08856 0.08438 -0.1415 0.8814 0.0450
-8.750 0.2336 0.08628 0.08210 -0.1419 0.8781 0.0456
-8.500 0.2507 0.08364 0.07945 -0.1441 0.8756 0.0465
-8.250 0.2516 0.08198 0.07781 -0.1427 0.8688 0.0472
-8.000 0.2558 0.07983 0.07566 -0.1429 0.8628 0.0485
-7.750 0.2381 0.07698 0.07282 -0.1456 0.8545 0.0504
-7.500 0.2346 0.07486 0.07073 -0.1442 0.8469 0.0506
-7.250 0.2598 0.07230 0.06815 -0.1456 0.8445 0.0511
-7.000 0.2849 0.06970 0.06551 -0.1483 0.8421 0.0520
-6.750 0.2697 0.06903 0.06488 -0.1430 0.8307 0.0525
-6.500 0.2879 0.06621 0.06201 -0.1463 0.8266 0.0542
-6.000 0.2926 0.06094 0.05670 -0.1489 0.8101 0.0582
-5.500 0.2841 0.04745 0.04293 -0.1554 0.7919 0.0395
-5.250 0.2846 0.04676 0.04225 -0.1517 0.7815 0.0398
-5.000 0.3070 0.04321 0.03857 -0.1547 0.7751 0.0380
-4.750 0.2814 0.02825 0.02225 -0.1594 0.7632 0.0348
-4.500 0.3064 0.02605 0.01955 -0.1600 0.7572 0.0346
-4.250 0.3221 0.02503 0.01846 -0.1581 0.7491 0.0350
-4.000 0.3429 0.02396 0.01722 -0.1572 0.7415 0.0354
-3.750 0.3706 0.02286 0.01591 -0.1575 0.7354 0.0360
-3.500 0.3835 0.02209 0.01493 -0.1547 0.7261 0.0363
-3.250 0.4136 0.02102 0.01355 -0.1551 0.7199 0.0363
-3.000 0.4280 0.02042 0.01277 -0.1525 0.7107 0.0363
-2.750 0.4557 0.01967 0.01179 -0.1523 0.7036 0.0363
-2.500 0.4756 0.01916 0.01112 -0.1506 0.6953 0.0365
-2.250 0.5010 0.01864 0.01043 -0.1500 0.6877 0.0366
-2.000 0.5248 0.01820 0.00987 -0.1491 0.6801 0.0368
-1.750 0.5476 0.01784 0.00940 -0.1479 0.6721 0.0372
-1.500 0.5747 0.01748 0.00892 -0.1476 0.6652 0.0375
-1.250 0.5945 0.01728 0.00865 -0.1459 0.6575 0.0377
-1.000 0.6209 0.01704 0.00830 -0.1455 0.6506 0.0383
-0.750 0.6420 0.01695 0.00814 -0.1440 0.6431 0.0391
-0.500 0.6640 0.01676 0.00795 -0.1429 0.6358 0.0401
-0.250 0.6896 0.01663 0.00777 -0.1423 0.6294 0.0409
0.000 0.7081 0.01664 0.00777 -0.1404 0.6221 0.0415
0.250 0.7317 0.01661 0.00767 -0.1395 0.6154 0.0421
0.500 0.7542 0.01663 0.00761 -0.1384 0.6086 0.0428
0.750 0.7740 0.01668 0.00762 -0.1368 0.6015 0.0435
1.000 0.7986 0.01670 0.00752 -0.1361 0.5950 0.0444
1.250 0.8191 0.01674 0.00753 -0.1347 0.5885 0.0456
1.500 0.8387 0.01681 0.00755 -0.1331 0.5812 0.0473
1.750 0.8632 0.01685 0.00750 -0.1324 0.5749 0.0510
2.000 0.8809 0.01693 0.00762 -0.1305 0.5678 0.0585
2.250 0.9016 0.01673 0.00797 -0.1295 0.5609 0.2235
2.500 0.9230 0.01700 0.00820 -0.1282 0.5546 0.2571
2.750 0.9395 0.01730 0.00849 -0.1261 0.5473 0.2725
3.000 0.9582 0.01765 0.00874 -0.1244 0.5402 0.2871
3.250 0.9756 0.01804 0.00914 -0.1224 0.5336 0.2962
3.500 0.9926 0.01836 0.00941 -0.1205 0.5264 0.3050
3.750 1.0120 0.01865 0.00964 -0.1190 0.5200 0.3108
4.000 1.0272 0.01902 0.01003 -0.1168 0.5127 0.3176
4.250 1.0445 0.01936 0.01029 -0.1150 0.5058 0.3256
4.500 1.0632 0.01962 0.01053 -0.1135 0.4997 0.3291
4.750 1.0801 0.01989 0.01080 -0.1117 0.4927 0.3311
5.000 1.0984 0.02015 0.01101 -0.1102 0.4862 0.3331
5.250 1.1165 0.02043 0.01127 -0.1087 0.4801 0.3348
5.500 1.1341 0.02072 0.01155 -0.1072 0.4738 0.3364
5.750 1.1528 0.02102 0.01179 -0.1059 0.4676 0.3382
6.000 1.1706 0.02135 0.01211 -0.1045 0.4619 0.3400
6.250 1.1876 0.02171 0.01246 -0.1029 0.4556 0.3416
6.500 1.2061 0.02204 0.01275 -0.1017 0.4501 0.3430
6.750 1.2239 0.02240 0.01314 -0.1004 0.4446 0.3445
7.000 1.2405 0.02281 0.01358 -0.0989 0.4387 0.3465
7.250 1.2580 0.02321 0.01397 -0.0976 0.4332 0.3486
7.500 1.2746 0.02365 0.01440 -0.0962 0.4276 0.3505
7.750 1.2896 0.02413 0.01493 -0.0945 0.4212 0.3525
8.000 1.3048 0.02464 0.01541 -0.0930 0.4150 0.3543
8.250 1.3209 0.02519 0.01597 -0.0917 0.4088 0.3561
8.500 1.3374 0.02576 0.01658 -0.0905 0.4029 0.3580
8.750 1.3559 0.02634 0.01717 -0.0898 0.3974 0.3596
9.000 1.3752 0.02692 0.01778 -0.0893 0.3927 0.3616
9.250 1.3921 0.02759 0.01853 -0.0885 0.3869 0.3637
9.500 1.4083 0.02827 0.01924 -0.0875 0.3815 0.3657
9.750 1.4250 0.02892 0.01987 -0.0866 0.3768 0.3686
10.000 1.4382 0.02971 0.02076 -0.0852 0.3710 0.3713
10.250 1.4519 0.03052 0.02162 -0.0840 0.3654 0.3734
10.500 1.4658 0.03133 0.02243 -0.0829 0.3599 0.3758
10.750 1.4778 0.03227 0.02346 -0.0816 0.3539 0.3781
11.000 1.4887 0.03326 0.02451 -0.0801 0.3477 0.3804
11.250 1.4990 0.03430 0.02552 -0.0787 0.3414 0.3829
11.500 1.5078 0.03548 0.02680 -0.0772 0.3346 0.3851
11.750 1.5178 0.03661 0.02798 -0.0758 0.3286 0.3874
12.000 1.5280 0.03777 0.02917 -0.0746 0.3233 0.3898
12.250 1.5380 0.03900 0.03051 -0.0734 0.3177 0.3926
12.500 1.5462 0.04034 0.03189 -0.0721 0.3119 0.3954
12.750 1.5538 0.04175 0.03332 -0.0708 0.3060 0.3988
13.000 1.5604 0.04332 0.03499 -0.0696 0.2993 0.4019
13.250 1.5646 0.04506 0.03674 -0.0682 0.2921 0.4052
13.500 1.5702 0.04679 0.03856 -0.0671 0.2854 0.4091
13.750 1.5731 0.04876 0.04055 -0.0658 0.2780 0.4127
14.000 1.5764 0.05076 0.04262 -0.0646 0.2708 0.4162
14.250 1.5775 0.05302 0.04493 -0.0635 0.2628 0.4195
14.500 1.5788 0.05529 0.04724 -0.0625 0.2556 0.4242
14.750 1.5801 0.05763 0.04965 -0.0615 0.2481 0.4296
15.000 1.5799 0.06018 0.05223 -0.0607 0.2412 0.4365
15.250 1.5796 0.06288 0.05504 -0.0600 0.2329 0.4528
15.750 1.6224 0.07153 0.06444 -0.0713 0.2116 1.0000
16.000 1.6209 0.07440 0.06739 -0.0707 0.2048 1.0000
16.250 1.6146 0.07784 0.07084 -0.0700 0.1979 1.0000
16.500 1.6125 0.08084 0.07391 -0.0695 0.1919 1.0000
16.750 1.6076 0.08421 0.07733 -0.0690 0.1858 1.0000
17.000 1.6023 0.08763 0.08079 -0.0686 0.1806 1.0000
17.250 1.5984 0.09095 0.08418 -0.0684 0.1743 1.0000
17.500 1.5918 0.09466 0.08793 -0.0682 0.1689 1.0000
17.750 1.5884 0.09797 0.09131 -0.0682 0.1641 1.0000
18.000 1.5835 0.10154 0.09495 -0.0682 0.1583 1.0000
18.250 1.5756 0.10550 0.09893 -0.0684 0.1532 1.0000
18.500 1.5725 0.10888 0.10240 -0.0687 0.1478 1.0000
18.750 1.5650 0.11287 0.10643 -0.0691 0.1417 1.0000
19.000 1.5593 0.11664 0.11026 -0.0696 0.1369 1.0000
19.250 1.5543 0.12036 0.11405 -0.0702 0.1308 1.0000
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