USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.12 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27-il-1000000-n5.txt Download as CSV file: xf-usa27-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2642 0.09868 0.09696 -0.0581 0.9897 0.0107
-10.250 -0.2544 0.09517 0.09345 -0.0609 0.9880 0.0110
-9.750 -0.2527 0.08261 0.08089 -0.0706 0.9833 0.0127
-9.500 -0.2417 0.07988 0.07816 -0.0731 0.9786 0.0128
-9.250 -0.2284 0.07687 0.07516 -0.0765 0.9750 0.0130
-9.000 -0.2187 0.07398 0.07227 -0.0791 0.9685 0.0132
-8.750 -0.2089 0.07040 0.06867 -0.0832 0.9608 0.0134
-8.500 -0.2046 0.06621 0.06446 -0.0880 0.9466 0.0137
-8.250 -0.2270 0.05002 0.04807 -0.1030 0.9247 0.0157
-8.000 -0.2128 0.04648 0.04441 -0.1055 0.9117 0.0159
-7.750 -0.1978 0.04285 0.04064 -0.1075 0.8959 0.0160
-7.500 -0.1834 0.03857 0.03618 -0.1093 0.8787 0.0163
-7.250 -0.1769 0.03040 0.02759 -0.1110 0.8641 0.0169
-7.000 -0.1681 0.02568 0.02242 -0.1102 0.8500 0.0176
-6.750 -0.1635 0.02014 0.01612 -0.1077 0.8373 0.0188
-6.500 -0.1448 0.01853 0.01412 -0.1063 0.8227 0.0191
-6.250 -0.1262 0.01698 0.01230 -0.1050 0.8089 0.0194
-6.000 -0.1034 0.01640 0.01159 -0.1042 0.7950 0.0196
-5.750 -0.0799 0.01595 0.01103 -0.1035 0.7809 0.0198
-5.500 -0.0567 0.01551 0.01046 -0.1026 0.7632 0.0200
-5.250 -0.0346 0.01501 0.00976 -0.1015 0.7364 0.0202
-5.000 -0.0138 0.01462 0.00914 -0.1001 0.6990 0.0204
-4.750 0.0075 0.01423 0.00853 -0.0988 0.6674 0.0206
-4.500 0.0302 0.01379 0.00791 -0.0978 0.6465 0.0207
-4.250 0.0539 0.01335 0.00731 -0.0969 0.6310 0.0209
-4.000 0.0781 0.01291 0.00674 -0.0962 0.6188 0.0211
-3.500 0.1281 0.01207 0.00568 -0.0949 0.6005 0.0215
-3.000 0.1791 0.01139 0.00485 -0.0939 0.5848 0.0220
-2.500 0.2302 0.01084 0.00415 -0.0928 0.5668 0.0224
-2.250 0.2555 0.01061 0.00386 -0.0923 0.5568 0.0227
-2.000 0.2808 0.01042 0.00360 -0.0917 0.5455 0.0229
-1.750 0.3064 0.01026 0.00339 -0.0912 0.5340 0.0231
-1.500 0.3318 0.01016 0.00323 -0.0906 0.5205 0.0233
-1.250 0.3567 0.01009 0.00309 -0.0900 0.5031 0.0234
-1.000 0.3797 0.00990 0.00278 -0.0890 0.4805 0.0238
-0.750 0.4030 0.00983 0.00261 -0.0881 0.4559 0.0241
-0.250 0.4511 0.00983 0.00243 -0.0866 0.4189 0.0247
0.000 0.4761 0.00981 0.00236 -0.0860 0.4061 0.0249
0.250 0.5015 0.00979 0.00230 -0.0855 0.3969 0.0252
0.500 0.5267 0.00979 0.00225 -0.0849 0.3885 0.0256
0.750 0.5525 0.00977 0.00222 -0.0845 0.3816 0.0262
1.000 0.5780 0.00978 0.00220 -0.0840 0.3742 0.0268
1.250 0.6037 0.00978 0.00218 -0.0836 0.3684 0.0272
1.500 0.6294 0.00980 0.00217 -0.0832 0.3614 0.0277
1.750 0.6548 0.00985 0.00218 -0.0827 0.3540 0.0282
2.000 0.6805 0.00989 0.00220 -0.0823 0.3468 0.0286
2.250 0.7058 0.00994 0.00222 -0.0818 0.3402 0.0295
2.500 0.7317 0.00997 0.00225 -0.0815 0.3355 0.0308
2.750 0.7575 0.01003 0.00229 -0.0811 0.3303 0.0321
3.000 0.7830 0.01010 0.00235 -0.0807 0.3253 0.0339
3.250 0.8075 0.00998 0.00244 -0.0801 0.3217 0.1529
3.500 0.8322 0.00988 0.00257 -0.0797 0.3180 0.2488
3.750 0.8572 0.00987 0.00270 -0.0792 0.3136 0.3153
4.000 0.8818 0.00991 0.00284 -0.0787 0.3084 0.3731
4.250 0.9034 0.00876 0.00315 -0.0777 0.3050 0.9625
4.500 0.9492 0.00898 0.00336 -0.0818 0.2997 0.9856
4.750 1.0049 0.00928 0.00359 -0.0883 0.2910 0.9956
5.000 1.0402 0.00949 0.00374 -0.0903 0.2800 0.9977
5.250 1.0737 0.00975 0.00392 -0.0919 0.2654 0.9994
5.500 1.0976 0.01002 0.00410 -0.0913 0.2490 1.0000
5.750 1.1138 0.01036 0.00432 -0.0891 0.2248 1.0000
6.000 1.1236 0.01101 0.00472 -0.0858 0.1834 1.0000
6.250 1.1371 0.01146 0.00505 -0.0831 0.1639 1.0000
6.500 1.1541 0.01174 0.00529 -0.0811 0.1551 1.0000
6.750 1.1714 0.01201 0.00553 -0.0791 0.1478 1.0000
7.000 1.1883 0.01231 0.00578 -0.0771 0.1387 1.0000
7.250 1.2035 0.01267 0.00607 -0.0748 0.1254 1.0000
7.500 1.2041 0.01362 0.00672 -0.0698 0.0793 1.0000
7.750 1.1995 0.01499 0.00780 -0.0641 0.0184 1.0000
8.000 1.2164 0.01537 0.00819 -0.0623 0.0155 1.0000
8.250 1.2341 0.01573 0.00857 -0.0607 0.0138 1.0000
8.500 1.2520 0.01610 0.00897 -0.0591 0.0128 1.0000
8.750 1.2693 0.01651 0.00940 -0.0576 0.0118 1.0000
9.000 1.2857 0.01699 0.00990 -0.0559 0.0109 1.0000
9.250 1.3019 0.01748 0.01043 -0.0542 0.0102 1.0000
9.500 1.3186 0.01795 0.01093 -0.0527 0.0098 1.0000
9.750 1.3349 0.01846 0.01148 -0.0512 0.0094 1.0000
10.000 1.3504 0.01901 0.01206 -0.0496 0.0089 1.0000
10.250 1.3654 0.01961 0.01269 -0.0480 0.0084 1.0000
10.500 1.3792 0.02030 0.01341 -0.0463 0.0079 1.0000
10.750 1.3913 0.02109 0.01425 -0.0445 0.0075 1.0000
11.000 1.4051 0.02181 0.01501 -0.0429 0.0073 1.0000
11.250 1.4180 0.02260 0.01585 -0.0413 0.0071 1.0000
11.500 1.4300 0.02346 0.01677 -0.0397 0.0068 1.0000
11.750 1.4414 0.02439 0.01775 -0.0382 0.0066 1.0000
12.000 1.4522 0.02540 0.01881 -0.0366 0.0064 1.0000
12.250 1.4622 0.02649 0.01995 -0.0351 0.0062 1.0000
12.500 1.4712 0.02769 0.02120 -0.0336 0.0060 1.0000
12.750 1.4789 0.02903 0.02261 -0.0322 0.0058 1.0000
13.000 1.4843 0.03061 0.02425 -0.0306 0.0056 1.0000
13.250 1.4867 0.03252 0.02624 -0.0291 0.0054 1.0000
13.500 1.4929 0.03417 0.02797 -0.0280 0.0053 1.0000
13.750 1.4980 0.03600 0.02987 -0.0270 0.0052 1.0000
14.000 1.5017 0.03803 0.03198 -0.0261 0.0051 1.0000
14.250 1.5042 0.04029 0.03433 -0.0254 0.0049 1.0000
14.500 1.5054 0.04281 0.03694 -0.0249 0.0048 1.0000
14.750 1.5054 0.04558 0.03980 -0.0246 0.0047 1.0000
15.000 1.5045 0.04854 0.04286 -0.0244 0.0047 1.0000
15.250 1.5020 0.05179 0.04620 -0.0244 0.0046 1.0000
15.500 1.4987 0.05521 0.04971 -0.0246 0.0045 1.0000
15.750 1.4935 0.05892 0.05352 -0.0248 0.0044 1.0000
16.000 1.4873 0.06281 0.05751 -0.0252 0.0044 1.0000
16.250 1.4796 0.06701 0.06181 -0.0258 0.0043 1.0000
16.500 1.4712 0.07141 0.06631 -0.0266 0.0043 1.0000
16.750 1.4612 0.07609 0.07110 -0.0275 0.0042 1.0000
17.000 1.4506 0.08094 0.07605 -0.0285 0.0042 1.0000
17.250 1.4394 0.08599 0.08120 -0.0297 0.0041 1.0000
17.500 1.4272 0.09124 0.08656 -0.0311 0.0041 1.0000
17.750 1.4148 0.09653 0.09195 -0.0325 0.0041 1.0000
18.000 1.4022 0.10193 0.09744 -0.0340 0.0040 1.0000
18.250 1.3897 0.10737 0.10298 -0.0357 0.0040 1.0000
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