USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 50,000 Max Cl/Cd: 35.51 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27-il-50000-n5.txt Download as CSV file: xf-usa27-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3482 0.10415 0.09809 -0.0229 1.0000 0.1425
-7.250 -0.3747 0.10384 0.09793 -0.0218 1.0000 0.1454
-7.000 -0.4003 0.10354 0.09774 -0.0234 1.0000 0.1467
-6.750 -0.3891 0.09880 0.09306 -0.0197 1.0000 0.1487
-6.500 -0.3866 0.09597 0.09028 -0.0172 1.0000 0.1515
-6.250 -0.3903 0.09372 0.08809 -0.0159 1.0000 0.1551
-6.000 -0.3862 0.09112 0.08544 -0.0243 0.9938 0.1631
-5.750 -0.3647 0.08668 0.08101 -0.0228 0.9892 0.1682
-5.500 -0.3428 0.08309 0.07731 -0.0310 0.9791 0.1797
-5.000 -0.2757 0.06673 0.06019 -0.0485 0.9629 0.0861
-4.750 -0.2445 0.05949 0.05229 -0.0551 0.9531 0.0752
-4.500 -0.2167 0.05596 0.04854 -0.0576 0.9455 0.0746
-4.250 -0.1874 0.05224 0.04446 -0.0603 0.9369 0.0746
-4.000 -0.1596 0.04905 0.04096 -0.0621 0.9278 0.0742
-3.750 -0.1256 0.04588 0.03744 -0.0647 0.9202 0.0731
-3.500 -0.0970 0.04310 0.03428 -0.0659 0.9095 0.0721
-3.250 -0.0610 0.04034 0.03104 -0.0680 0.9010 0.0713
-3.000 -0.0266 0.03801 0.02823 -0.0694 0.8909 0.0708
-2.750 0.0054 0.03616 0.02592 -0.0702 0.8797 0.0717
-2.500 0.0444 0.03445 0.02370 -0.0720 0.8712 0.0736
-2.250 0.0787 0.03308 0.02194 -0.0728 0.8605 0.0745
-2.000 0.1110 0.03192 0.02047 -0.0733 0.8491 0.0749
-1.750 0.1550 0.03049 0.01882 -0.0756 0.8425 0.0758
-1.500 0.1867 0.02958 0.01778 -0.0759 0.8302 0.0771
-1.250 0.2215 0.02878 0.01682 -0.0766 0.8189 0.0790
-1.000 0.2635 0.02786 0.01575 -0.0786 0.8108 0.0829
-0.750 0.2937 0.02732 0.01506 -0.0785 0.7980 0.0881
-0.500 0.3229 0.02674 0.01448 -0.0783 0.7850 0.0941
-0.250 0.3529 0.02622 0.01391 -0.0782 0.7725 0.1016
0.000 0.3841 0.02556 0.01341 -0.0783 0.7606 0.1198
0.250 0.4150 0.02472 0.01316 -0.0785 0.7493 0.2685
0.500 0.4398 0.02407 0.01286 -0.0777 0.7353 0.4002
0.750 0.5206 0.02262 0.01245 -0.0871 0.7219 1.0000
1.000 0.5488 0.02260 0.01216 -0.0866 0.7073 1.0000
1.250 0.5773 0.02260 0.01190 -0.0863 0.6929 1.0000
1.500 0.6060 0.02262 0.01168 -0.0860 0.6786 1.0000
1.750 0.6346 0.02269 0.01151 -0.0857 0.6644 1.0000
2.000 0.6630 0.02280 0.01141 -0.0855 0.6505 1.0000
2.250 0.6913 0.02296 0.01136 -0.0853 0.6371 1.0000
2.500 0.7201 0.02315 0.01134 -0.0851 0.6241 1.0000
2.750 0.7440 0.02349 0.01156 -0.0843 0.6103 1.0000
3.000 0.7672 0.02387 0.01183 -0.0834 0.5971 1.0000
3.250 0.7911 0.02427 0.01214 -0.0827 0.5849 1.0000
3.500 0.8168 0.02462 0.01238 -0.0822 0.5737 1.0000
3.750 0.8395 0.02506 0.01276 -0.0813 0.5623 1.0000
4.000 0.8605 0.02557 0.01325 -0.0802 0.5513 1.0000
4.250 0.8858 0.02597 0.01358 -0.0797 0.5420 1.0000
4.500 0.9066 0.02649 0.01411 -0.0786 0.5318 1.0000
4.750 0.9280 0.02702 0.01465 -0.0776 0.5226 1.0000
5.000 0.9523 0.02746 0.01506 -0.0769 0.5142 1.0000
5.250 0.9709 0.02807 0.01572 -0.0755 0.5046 1.0000
5.500 0.9957 0.02842 0.01602 -0.0749 0.4959 1.0000
5.750 1.0133 0.02898 0.01665 -0.0733 0.4854 1.0000
6.000 1.0322 0.02947 0.01716 -0.0718 0.4750 1.0000
6.250 1.0555 0.02977 0.01740 -0.0708 0.4650 1.0000
6.500 1.0718 0.03032 0.01805 -0.0690 0.4540 1.0000
6.750 1.0899 0.03090 0.01868 -0.0675 0.4443 1.0000
7.000 1.1132 0.03135 0.01914 -0.0667 0.4362 1.0000
7.250 1.1281 0.03215 0.02008 -0.0649 0.4273 1.0000
7.500 1.1533 0.03257 0.02052 -0.0644 0.4196 1.0000
7.750 1.1647 0.03351 0.02165 -0.0621 0.4105 1.0000
8.000 1.1894 0.03399 0.02215 -0.0616 0.4030 1.0000
8.250 1.1990 0.03503 0.02341 -0.0592 0.3940 1.0000
8.500 1.2208 0.03561 0.02407 -0.0583 0.3861 1.0000
8.750 1.2303 0.03663 0.02530 -0.0559 0.3768 1.0000
9.000 1.2468 0.03740 0.02617 -0.0543 0.3684 1.0000
9.250 1.2583 0.03834 0.02728 -0.0522 0.3594 1.0000
9.500 1.2696 0.03937 0.02846 -0.0501 0.3511 1.0000
9.750 1.2825 0.04019 0.02944 -0.0481 0.3422 1.0000
10.000 1.2826 0.04141 0.03084 -0.0446 0.3326 1.0000
10.250 1.2919 0.04189 0.03134 -0.0419 0.3217 1.0000
10.500 1.2892 0.04306 0.03264 -0.0383 0.3109 1.0000
10.750 1.2832 0.04459 0.03432 -0.0348 0.3003 1.0000
11.000 1.2837 0.04568 0.03548 -0.0321 0.2897 1.0000
11.250 1.2798 0.04728 0.03719 -0.0294 0.2794 1.0000
11.500 1.2697 0.04984 0.03996 -0.0270 0.2702 1.0000
11.750 1.2726 0.05132 0.04152 -0.0253 0.2619 1.0000
12.000 1.2604 0.05470 0.04513 -0.0238 0.2541 1.0000
12.250 1.2569 0.05712 0.04766 -0.0226 0.2459 1.0000
12.500 1.2472 0.06043 0.05113 -0.0218 0.2372 1.0000
12.750 1.2337 0.06461 0.05547 -0.0216 0.2292 1.0000
13.000 1.2310 0.06727 0.05818 -0.0212 0.2199 1.0000
13.250 1.2108 0.07308 0.06422 -0.0220 0.2136 1.0000
13.500 1.2148 0.07511 0.06631 -0.0217 0.2065 1.0000
13.750 1.1903 0.08208 0.07349 -0.0233 0.2011 1.0000
14.000 1.1937 0.08415 0.07558 -0.0232 0.1917 1.0000
14.250 1.1717 0.09111 0.08273 -0.0251 0.1863 1.0000
14.500 1.1735 0.09353 0.08520 -0.0253 0.1758 1.0000
14.750 1.1575 0.09965 0.09149 -0.0272 0.1699 1.0000
15.000 1.1563 0.10290 0.09480 -0.0279 0.1607 1.0000
15.250 1.1424 0.10879 0.10083 -0.0299 0.1527 1.0000
15.500 1.1295 0.11465 0.10680 -0.0320 0.1446 1.0000
15.750 1.1190 0.12021 0.11250 -0.0341 0.1361 1.0000
16.000 1.0989 0.12810 0.12053 -0.0375 0.1302 1.0000
16.250 1.0873 0.13426 0.12680 -0.0402 0.1205 1.0000
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Polar data table (+)
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