USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 100,000 Max Cl/Cd: 48.6 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27m2-il-100000-n5.txt Download as CSV file: xf-usa27m2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2854 0.10250 0.09779 -0.0424 0.9869 0.0826
-8.250 -0.2929 0.09859 0.09392 -0.0500 0.9792 0.0862
-8.000 -0.3080 0.09382 0.08913 -0.0601 0.9668 0.0871
-7.500 -0.2737 0.08551 0.08083 -0.0623 0.9600 0.0885
-7.000 -0.2755 0.06860 0.06357 -0.0721 0.9412 0.0557
-6.500 -0.2708 0.05329 0.04754 -0.0770 0.9243 0.0484
-6.250 -0.2519 0.05005 0.04415 -0.0779 0.9187 0.0479
-6.000 -0.2359 0.04654 0.04039 -0.0782 0.9125 0.0474
-5.750 -0.2225 0.04320 0.03671 -0.0775 0.9046 0.0469
-5.500 -0.1979 0.03957 0.03259 -0.0786 0.9005 0.0468
-5.250 -0.1849 0.03716 0.02974 -0.0767 0.8902 0.0472
-5.000 -0.1536 0.03452 0.02658 -0.0778 0.8852 0.0476
-4.750 -0.1326 0.03268 0.02440 -0.0766 0.8745 0.0477
-4.500 -0.0956 0.03053 0.02186 -0.0782 0.8689 0.0475
-4.250 -0.0724 0.02908 0.02013 -0.0770 0.8578 0.0475
-4.000 -0.0350 0.02745 0.01821 -0.0785 0.8526 0.0476
-3.750 -0.0120 0.02641 0.01698 -0.0773 0.8422 0.0478
-3.500 0.0250 0.02516 0.01552 -0.0786 0.8365 0.0480
-3.250 0.0497 0.02432 0.01455 -0.0777 0.8258 0.0483
-3.000 0.0860 0.02322 0.01339 -0.0790 0.8194 0.0493
-2.750 0.1097 0.02255 0.01273 -0.0781 0.8076 0.0506
-2.500 0.1424 0.02178 0.01191 -0.0787 0.7989 0.0521
-2.250 0.1699 0.02116 0.01123 -0.0783 0.7872 0.0530
-2.000 0.1955 0.02064 0.01066 -0.0776 0.7742 0.0538
-1.750 0.2239 0.02012 0.01007 -0.0773 0.7614 0.0547
-1.500 0.2538 0.01965 0.00949 -0.0773 0.7484 0.0558
-1.250 0.2837 0.01916 0.00894 -0.0774 0.7345 0.0574
-1.000 0.3132 0.01876 0.00846 -0.0774 0.7193 0.0597
-0.750 0.3434 0.01843 0.00802 -0.0775 0.7032 0.0638
0.000 0.4368 0.01723 0.00722 -0.0787 0.6540 0.2394
0.250 0.4652 0.01719 0.00719 -0.0787 0.6380 0.2933
0.500 0.4923 0.01720 0.00712 -0.0784 0.6221 0.3251
0.750 0.5181 0.01718 0.00707 -0.0779 0.6064 0.3621
1.000 0.5418 0.01710 0.00701 -0.0771 0.5909 0.4013
1.500 0.7163 0.01672 0.00761 -0.1011 0.5480 1.0000
1.750 0.7362 0.01693 0.00767 -0.0996 0.5339 1.0000
2.000 0.7556 0.01715 0.00775 -0.0979 0.5200 1.0000
2.250 0.7752 0.01737 0.00784 -0.0963 0.5073 1.0000
2.500 0.7948 0.01761 0.00793 -0.0947 0.4959 1.0000
2.750 0.8145 0.01787 0.00805 -0.0931 0.4853 1.0000
3.000 0.8340 0.01812 0.00820 -0.0916 0.4753 1.0000
3.500 0.8735 0.01868 0.00856 -0.0885 0.4580 1.0000
4.000 0.9127 0.01928 0.00898 -0.0855 0.4422 1.0000
4.250 0.9325 0.01961 0.00919 -0.0840 0.4349 1.0000
4.500 0.9513 0.01992 0.00947 -0.0824 0.4271 1.0000
4.750 0.9706 0.02025 0.00972 -0.0809 0.4202 1.0000
5.000 0.9906 0.02059 0.01002 -0.0795 0.4141 1.0000
5.250 1.0094 0.02092 0.01035 -0.0779 0.4076 1.0000
5.500 1.0294 0.02128 0.01063 -0.0766 0.4018 1.0000
5.750 1.0481 0.02163 0.01098 -0.0750 0.3958 1.0000
6.000 1.0661 0.02198 0.01136 -0.0733 0.3896 1.0000
6.250 1.0861 0.02235 0.01168 -0.0720 0.3845 1.0000
6.500 1.1045 0.02273 0.01209 -0.0704 0.3793 1.0000
6.750 1.1221 0.02310 0.01253 -0.0687 0.3739 1.0000
7.000 1.1409 0.02348 0.01290 -0.0672 0.3688 1.0000
7.250 1.1599 0.02389 0.01331 -0.0658 0.3639 1.0000
7.500 1.1753 0.02429 0.01381 -0.0637 0.3582 1.0000
7.750 1.1923 0.02468 0.01425 -0.0620 0.3529 1.0000
8.000 1.2117 0.02511 0.01464 -0.0607 0.3483 1.0000
8.250 1.2250 0.02556 0.01524 -0.0583 0.3427 1.0000
8.500 1.2395 0.02599 0.01576 -0.0562 0.3374 1.0000
8.750 1.2566 0.02642 0.01618 -0.0545 0.3327 1.0000
9.000 1.2688 0.02693 0.01681 -0.0521 0.3272 1.0000
9.250 1.2810 0.02743 0.01743 -0.0497 0.3214 1.0000
9.500 1.2959 0.02791 0.01792 -0.0478 0.3163 1.0000
9.750 1.3060 0.02850 0.01866 -0.0452 0.3100 1.0000
10.000 1.3141 0.02906 0.01930 -0.0424 0.3025 1.0000
10.250 1.3216 0.02968 0.01997 -0.0396 0.2947 1.0000
10.500 1.3267 0.03037 0.02075 -0.0366 0.2857 1.0000
10.750 1.3317 0.03117 0.02165 -0.0338 0.2766 1.0000
11.000 1.3369 0.03200 0.02252 -0.0312 0.2681 1.0000
11.250 1.3424 0.03300 0.02367 -0.0288 0.2591 1.0000
11.500 1.3467 0.03406 0.02476 -0.0264 0.2507 1.0000
11.750 1.3502 0.03529 0.02610 -0.0242 0.2413 1.0000
12.000 1.3538 0.03662 0.02752 -0.0221 0.2329 1.0000
12.250 1.3566 0.03807 0.02904 -0.0202 0.2254 1.0000
12.500 1.3590 0.03969 0.03076 -0.0184 0.2177 1.0000
12.750 1.3577 0.04158 0.03266 -0.0166 0.2099 1.0000
13.000 1.3561 0.04370 0.03487 -0.0151 0.2012 1.0000
13.250 1.3521 0.04610 0.03730 -0.0137 0.1939 1.0000
13.500 1.3490 0.04863 0.03992 -0.0126 0.1873 1.0000
13.750 1.3435 0.05147 0.04279 -0.0116 0.1818 1.0000
14.000 1.3394 0.05444 0.04590 -0.0110 0.1761 1.0000
14.250 1.3318 0.05788 0.04941 -0.0106 0.1702 1.0000
14.500 1.3225 0.06166 0.05325 -0.0105 0.1644 1.0000
14.750 1.3125 0.06578 0.05752 -0.0108 0.1581 1.0000
15.000 1.3011 0.07012 0.06192 -0.0111 0.1529 1.0000
15.250 1.2909 0.07458 0.06653 -0.0118 0.1478 1.0000
15.500 1.2792 0.07939 0.07150 -0.0127 0.1424 1.0000
15.750 1.2668 0.08431 0.07650 -0.0137 0.1373 1.0000
16.000 1.2548 0.08949 0.08189 -0.0150 0.1309 1.0000
16.250 1.2414 0.09486 0.08738 -0.0165 0.1241 1.0000
16.500 1.2305 0.10001 0.09271 -0.0179 0.1167 1.0000
16.750 1.2193 0.10525 0.09807 -0.0195 0.1081 1.0000
17.000 1.2074 0.11056 0.10344 -0.0212 0.0967 1.0000
17.250 1.1927 0.11633 0.10915 -0.0232 0.0841 1.0000
17.500 1.1751 0.12272 0.11546 -0.0256 0.0686 1.0000
17.750 1.1535 0.12994 0.12255 -0.0285 0.0469 1.0000
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Polar data table (+)
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