USA 48 AIRFOIL (usa48-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: USA 48 AIRFOIL (usa48-il) Reynolds number: 100,000 Max Cl/Cd: 49.31 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa48-il-100000-n5.txt Download as CSV file: xf-usa48-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 48 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5165 0.08856 0.08329 -0.0605 1.0000 0.0330
-12.000 -0.5706 0.07547 0.07008 -0.0689 1.0000 0.0318
-11.750 -0.6140 0.06713 0.06156 -0.0737 1.0000 0.0312
-11.500 -0.6463 0.06209 0.05639 -0.0749 1.0000 0.0310
-11.250 -0.6754 0.05840 0.05256 -0.0741 1.0000 0.0309
-11.000 -0.7029 0.05576 0.04980 -0.0714 1.0000 0.0308
-10.750 -0.7298 0.05393 0.04786 -0.0667 1.0000 0.0309
-10.500 -0.7496 0.05209 0.04590 -0.0623 1.0000 0.0310
-10.250 -0.7627 0.05013 0.04379 -0.0584 1.0000 0.0314
-10.000 -0.7724 0.04819 0.04168 -0.0548 1.0000 0.0320
-9.750 -0.7795 0.04623 0.03949 -0.0513 1.0000 0.0328
-9.500 -0.7849 0.04421 0.03717 -0.0478 1.0000 0.0337
-9.250 -0.7732 0.04139 0.03364 -0.0479 0.9953 0.0354
-9.000 -0.7484 0.03930 0.03152 -0.0492 0.9909 0.0368
-8.750 -0.7222 0.03735 0.02936 -0.0505 0.9861 0.0385
-8.500 -0.6980 0.03562 0.02722 -0.0512 0.9805 0.0412
-8.250 -0.6704 0.03378 0.02515 -0.0523 0.9756 0.0435
-8.000 -0.6431 0.03220 0.02348 -0.0531 0.9703 0.0458
-7.750 -0.6140 0.03091 0.02193 -0.0541 0.9647 0.0490
-7.500 -0.5851 0.02936 0.02034 -0.0550 0.9593 0.0519
-7.250 -0.5573 0.02807 0.01906 -0.0557 0.9527 0.0546
-7.000 -0.5263 0.02699 0.01782 -0.0568 0.9470 0.0582
-6.750 -0.5024 0.02579 0.01666 -0.0568 0.9388 0.0610
-6.500 -0.4712 0.02478 0.01562 -0.0580 0.9336 0.0647
-6.250 -0.4486 0.02401 0.01475 -0.0574 0.9244 0.0678
-6.000 -0.4163 0.02311 0.01383 -0.0588 0.9197 0.0714
-5.750 -0.3941 0.02251 0.01319 -0.0581 0.9103 0.0757
-5.500 -0.3613 0.02181 0.01248 -0.0593 0.9052 0.0821
-5.250 -0.3363 0.02125 0.01187 -0.0589 0.8968 0.0907
-5.000 -0.3056 0.02059 0.01114 -0.0596 0.8907 0.1075
-4.500 -0.2536 0.01902 0.01014 -0.0596 0.8761 0.2207
-4.250 -0.2180 0.01854 0.00971 -0.0612 0.8718 0.2620
-4.000 -0.1957 0.01828 0.00949 -0.0602 0.8616 0.2882
-3.750 -0.1602 0.01792 0.00914 -0.0616 0.8566 0.3154
-3.500 -0.1357 0.01771 0.00891 -0.0609 0.8469 0.3358
-3.250 -0.1005 0.01740 0.00857 -0.0623 0.8411 0.3593
-3.000 -0.0747 0.01717 0.00837 -0.0619 0.8317 0.3822
-2.750 -0.0407 0.01682 0.00806 -0.0630 0.8253 0.4126
-2.500 -0.0147 0.01657 0.00786 -0.0626 0.8159 0.4390
-2.250 0.0186 0.01621 0.00758 -0.0636 0.8091 0.4719
-2.000 0.0429 0.01594 0.00753 -0.0627 0.7994 0.5151
-1.750 0.0741 0.01572 0.00768 -0.0626 0.7926 0.5884
-1.500 0.0979 0.01578 0.00775 -0.0615 0.7823 0.6485
-1.250 0.1319 0.01573 0.00758 -0.0623 0.7752 0.6828
-1.000 0.1576 0.01574 0.00755 -0.0616 0.7647 0.7042
-0.750 0.1890 0.01569 0.00743 -0.0620 0.7563 0.7238
-0.500 0.2187 0.01564 0.00733 -0.0620 0.7469 0.7409
-0.250 0.2476 0.01562 0.00726 -0.0620 0.7372 0.7557
0.000 0.2808 0.01555 0.00712 -0.0628 0.7282 0.7696
0.250 0.3068 0.01556 0.00709 -0.0622 0.7167 0.7830
0.500 0.3360 0.01554 0.00702 -0.0622 0.7056 0.7975
0.750 0.3667 0.01550 0.00694 -0.0623 0.6947 0.8137
1.000 0.3918 0.01552 0.00698 -0.0615 0.6819 0.8306
1.250 0.4198 0.01554 0.00700 -0.0612 0.6694 0.8471
1.500 0.4500 0.01557 0.00701 -0.0614 0.6573 0.8613
1.750 0.4830 0.01563 0.00705 -0.0622 0.6457 0.8752
2.000 0.5151 0.01572 0.00713 -0.0630 0.6314 0.8899
2.250 0.5498 0.01582 0.00723 -0.0644 0.6180 0.9043
2.500 0.5862 0.01594 0.00733 -0.0661 0.6047 0.9195
2.750 0.6241 0.01607 0.00744 -0.0682 0.5923 0.9350
3.000 0.6627 0.01621 0.00753 -0.0706 0.5804 0.9509
3.250 0.7006 0.01638 0.00771 -0.0729 0.5682 0.9667
3.500 0.7371 0.01655 0.00787 -0.0751 0.5564 0.9830
3.750 0.7730 0.01675 0.00804 -0.0772 0.5449 0.9998
4.000 0.7861 0.01688 0.00814 -0.0747 0.5349 1.0000
4.250 0.8011 0.01706 0.00828 -0.0724 0.5242 1.0000
4.500 0.8179 0.01725 0.00841 -0.0704 0.5131 1.0000
4.750 0.8346 0.01747 0.00861 -0.0684 0.5015 1.0000
5.000 0.8518 0.01770 0.00884 -0.0665 0.4904 1.0000
5.250 0.8701 0.01794 0.00907 -0.0648 0.4799 1.0000
5.500 0.8876 0.01820 0.00931 -0.0629 0.4682 1.0000
5.750 0.9047 0.01847 0.00962 -0.0610 0.4564 1.0000
6.000 0.9222 0.01875 0.00991 -0.0592 0.4451 1.0000
6.250 0.9386 0.01904 0.01019 -0.0571 0.4321 1.0000
6.500 0.9542 0.01935 0.01048 -0.0550 0.4188 1.0000
6.750 0.9697 0.01968 0.01085 -0.0528 0.4056 1.0000
7.000 0.9835 0.02002 0.01120 -0.0504 0.3917 1.0000
7.250 0.9965 0.02040 0.01156 -0.0478 0.3780 1.0000
7.500 1.0103 0.02081 0.01197 -0.0454 0.3661 1.0000
7.750 1.0237 0.02125 0.01243 -0.0430 0.3546 1.0000
8.000 1.0373 0.02172 0.01292 -0.0407 0.3429 1.0000
8.250 1.0506 0.02222 0.01346 -0.0385 0.3311 1.0000
8.500 1.0631 0.02278 0.01404 -0.0362 0.3194 1.0000
8.750 1.0747 0.02338 0.01466 -0.0338 0.3077 1.0000
9.000 1.0859 0.02403 0.01536 -0.0314 0.2952 1.0000
9.250 1.0952 0.02475 0.01611 -0.0289 0.2806 1.0000
9.500 1.1027 0.02557 0.01693 -0.0262 0.2646 1.0000
9.750 1.1087 0.02649 0.01784 -0.0235 0.2477 1.0000
10.000 1.1140 0.02751 0.01884 -0.0209 0.2311 1.0000
10.250 1.1196 0.02860 0.01991 -0.0185 0.2159 1.0000
10.500 1.1251 0.02976 0.02110 -0.0163 0.2021 1.0000
10.750 1.1299 0.03102 0.02236 -0.0142 0.1889 1.0000
11.000 1.1333 0.03243 0.02376 -0.0121 0.1760 1.0000
11.250 1.1360 0.03397 0.02529 -0.0102 0.1648 1.0000
11.500 1.1377 0.03566 0.02698 -0.0084 0.1552 1.0000
11.750 1.1393 0.03746 0.02878 -0.0068 0.1464 1.0000
12.000 1.1405 0.03938 0.03075 -0.0054 0.1382 1.0000
12.250 1.1390 0.04161 0.03300 -0.0041 0.1306 1.0000
12.500 1.1407 0.04369 0.03519 -0.0031 0.1225 1.0000
12.750 1.1350 0.04650 0.03799 -0.0021 0.1142 1.0000
13.000 1.1369 0.04881 0.04047 -0.0015 0.1022 1.0000
13.250 1.1393 0.05118 0.04298 -0.0011 0.0670 1.0000
13.500 1.1252 0.05531 0.04687 -0.0010 0.0581 1.0000
13.750 1.1141 0.05932 0.05085 -0.0009 0.0531 1.0000
14.000 1.1029 0.06352 0.05508 -0.0012 0.0498 1.0000
14.250 1.0935 0.06768 0.05933 -0.0016 0.0470 1.0000
14.500 1.0862 0.07173 0.06352 -0.0022 0.0447 1.0000
14.750 1.0778 0.07604 0.06796 -0.0030 0.0427 1.0000
15.000 1.0679 0.08067 0.07270 -0.0040 0.0411 1.0000
15.250 1.0571 0.08556 0.07768 -0.0053 0.0398 1.0000
15.500 1.0496 0.09007 0.08231 -0.0065 0.0384 1.0000
15.750 1.0447 0.09429 0.08668 -0.0077 0.0370 1.0000
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