GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 395 AIRFOIL (goe395-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.23 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe395-il-1000000-n5.txt Download as CSV file: xf-goe395-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 395 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2028 0.09791 0.09531 -0.0392 0.7238 0.0062
-9.750 -0.2962 0.10816 0.10546 -0.0292 0.7269 0.0059
-6.750 -0.0687 0.01595 0.01182 -0.1456 0.7124 0.0204
-6.500 -0.0398 0.01505 0.01077 -0.1463 0.7113 0.0207
-6.250 -0.0114 0.01469 0.01032 -0.1466 0.7103 0.0209
-5.750 0.0470 0.01272 0.00801 -0.1482 0.7086 0.0227
-5.500 0.0755 0.01249 0.00775 -0.1484 0.7079 0.0233
-5.250 0.1042 0.01217 0.00736 -0.1486 0.7072 0.0240
-5.000 0.1331 0.01169 0.00677 -0.1489 0.7065 0.0245
-4.750 0.1620 0.01127 0.00625 -0.1492 0.7056 0.0251
-4.500 0.1909 0.01080 0.00566 -0.1495 0.7043 0.0256
-4.250 0.2199 0.01035 0.00509 -0.1497 0.7025 0.0260
-4.000 0.2488 0.00994 0.00457 -0.1499 0.7003 0.0262
-3.750 0.2776 0.00959 0.00411 -0.1501 0.6984 0.0265
-3.500 0.3064 0.00928 0.00371 -0.1502 0.6966 0.0267
-3.250 0.3351 0.00902 0.00336 -0.1503 0.6950 0.0270
-3.000 0.3639 0.00879 0.00306 -0.1504 0.6932 0.0272
-2.750 0.3927 0.00859 0.00281 -0.1505 0.6915 0.0275
-2.500 0.4215 0.00842 0.00262 -0.1505 0.6894 0.0277
-2.250 0.4502 0.00825 0.00241 -0.1506 0.6871 0.0279
-2.000 0.4791 0.00799 0.00209 -0.1507 0.6846 0.0286
-1.750 0.5078 0.00780 0.00185 -0.1507 0.6821 0.0297
-1.500 0.5364 0.00768 0.00169 -0.1508 0.6798 0.0309
-1.250 0.5651 0.00758 0.00158 -0.1508 0.6779 0.0319
-1.000 0.5938 0.00748 0.00148 -0.1509 0.6760 0.0330
-0.750 0.6224 0.00739 0.00141 -0.1509 0.6737 0.0340
-0.500 0.6510 0.00732 0.00134 -0.1509 0.6709 0.0352
-0.250 0.6795 0.00726 0.00127 -0.1509 0.6679 0.0368
0.000 0.7079 0.00720 0.00123 -0.1509 0.6648 0.0434
0.250 0.7365 0.00712 0.00122 -0.1510 0.6609 0.0582
0.500 0.7649 0.00708 0.00123 -0.1510 0.6546 0.0677
0.750 0.7931 0.00708 0.00122 -0.1510 0.6480 0.0711
1.000 0.8215 0.00705 0.00123 -0.1510 0.6416 0.0771
1.250 0.8497 0.00705 0.00123 -0.1510 0.6329 0.0799
1.500 0.8776 0.00707 0.00122 -0.1509 0.6145 0.0821
1.750 0.9034 0.00737 0.00127 -0.1505 0.5541 0.0838
2.000 0.9290 0.00777 0.00145 -0.1502 0.5113 0.0851
2.250 0.9556 0.00801 0.00160 -0.1500 0.4864 0.0897
2.500 0.9826 0.00817 0.00174 -0.1499 0.4698 0.0953
2.750 1.0096 0.00834 0.00186 -0.1497 0.4542 0.0987
3.000 1.0366 0.00850 0.00199 -0.1496 0.4390 0.1030
3.250 1.0633 0.00869 0.00214 -0.1494 0.4201 0.1103
3.500 1.0891 0.00898 0.00233 -0.1492 0.3916 0.1201
3.750 1.1149 0.00926 0.00254 -0.1489 0.3664 0.1356
4.000 1.1413 0.00945 0.00274 -0.1487 0.3491 0.1664
4.250 1.1674 0.00964 0.00295 -0.1485 0.3307 0.2171
4.500 1.1938 0.00961 0.00336 -0.1486 0.3117 0.5311
4.750 1.2191 0.00992 0.00362 -0.1483 0.2909 0.5620
5.000 1.2437 0.01030 0.00389 -0.1478 0.2635 0.5798
5.250 1.2643 0.01113 0.00440 -0.1469 0.1982 0.5951
5.750 1.3031 0.01192 0.00541 -0.1443 0.1147 1.0000
6.000 1.3272 0.01231 0.00573 -0.1438 0.1030 1.0000
6.250 1.3513 0.01267 0.00605 -0.1433 0.0922 1.0000
6.750 1.3958 0.01375 0.00690 -0.1417 0.0553 1.0000
7.000 1.4188 0.01418 0.00730 -0.1410 0.0467 1.0000
7.250 1.4408 0.01469 0.00775 -0.1402 0.0366 1.0000
7.500 1.4588 0.01557 0.00847 -0.1388 0.0161 1.0000
7.750 1.4803 0.01606 0.00897 -0.1379 0.0126 1.0000
8.000 1.5016 0.01654 0.00948 -0.1369 0.0109 1.0000
8.250 1.5218 0.01709 0.01006 -0.1358 0.0094 1.0000
8.500 1.5425 0.01757 0.01056 -0.1348 0.0088 1.0000
8.750 1.5623 0.01808 0.01111 -0.1336 0.0081 1.0000
9.000 1.5810 0.01864 0.01170 -0.1323 0.0075 1.0000
9.250 1.5981 0.01930 0.01239 -0.1308 0.0068 1.0000
9.500 1.6132 0.01994 0.01308 -0.1289 0.0063 1.0000
9.750 1.6278 0.02056 0.01374 -0.1269 0.0060 1.0000
10.000 1.6415 0.02126 0.01449 -0.1249 0.0057 1.0000
10.250 1.6546 0.02202 0.01530 -0.1230 0.0054 1.0000
10.500 1.6671 0.02286 0.01620 -0.1210 0.0052 1.0000
10.750 1.6788 0.02380 0.01718 -0.1191 0.0049 1.0000
11.000 1.6893 0.02487 0.01832 -0.1172 0.0047 1.0000
11.250 1.6971 0.02621 0.01973 -0.1150 0.0044 1.0000
11.500 1.7078 0.02735 0.02094 -0.1134 0.0043 1.0000
11.750 1.7180 0.02856 0.02222 -0.1117 0.0042 1.0000
12.000 1.7275 0.02985 0.02359 -0.1101 0.0041 1.0000
12.250 1.7364 0.03125 0.02506 -0.1085 0.0039 1.0000
12.500 1.7448 0.03270 0.02658 -0.1070 0.0038 1.0000
12.750 1.7526 0.03423 0.02818 -0.1055 0.0036 1.0000
13.000 1.7599 0.03584 0.02986 -0.1041 0.0035 1.0000
13.250 1.7659 0.03757 0.03169 -0.1026 0.0034 1.0000
13.500 1.7710 0.03943 0.03362 -0.1012 0.0033 1.0000
13.750 1.7748 0.04144 0.03571 -0.0997 0.0032 1.0000
14.000 1.7771 0.04362 0.03797 -0.0983 0.0031 1.0000
14.250 1.7769 0.04609 0.04054 -0.0968 0.0030 1.0000
14.500 1.7743 0.04887 0.04342 -0.0953 0.0029 1.0000
14.750 1.7704 0.05187 0.04654 -0.0940 0.0028 1.0000
15.000 1.7697 0.05461 0.04937 -0.0929 0.0028 1.0000
15.250 1.7683 0.05752 0.05240 -0.0920 0.0028 1.0000
15.500 1.7658 0.06067 0.05565 -0.0912 0.0028 1.0000
15.750 1.7624 0.06401 0.05911 -0.0906 0.0027 1.0000
16.000 1.7578 0.06763 0.06284 -0.0902 0.0027 1.0000
16.250 1.7528 0.07146 0.06679 -0.0900 0.0026 1.0000
16.500 1.7464 0.07563 0.07110 -0.0901 0.0026 1.0000
16.750 1.7393 0.08003 0.07562 -0.0905 0.0026 1.0000
17.000 1.7309 0.08475 0.08046 -0.0911 0.0025 1.0000
17.250 1.7209 0.08988 0.08572 -0.0920 0.0025 1.0000
17.500 1.7106 0.09518 0.09115 -0.0931 0.0025 1.0000
17.750 1.6988 0.10082 0.09692 -0.0946 0.0025 1.0000
18.000 1.6866 0.10659 0.10281 -0.0962 0.0024 1.0000
18.250 1.6736 0.11260 0.10895 -0.0981 0.0024 1.0000
18.500 1.6596 0.11890 0.11538 -0.1003 0.0024 1.0000
18.750 1.6464 0.12519 0.12179 -0.1028 0.0024 1.0000
19.000 1.6325 0.13166 0.12839 -0.1054 0.0024 1.0000
19.250 1.6179 0.13844 0.13530 -0.1085 0.0024 1.0000
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