GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 615 AIRFOIL (goe615-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.5 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe615-il-1000000.txt Download as CSV file: xf-goe615-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 615 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1633 0.08549 0.08373 -0.0804 0.9597 0.0289
-10.000 -0.1537 0.07909 0.07732 -0.0869 0.9516 0.0292
-9.750 -0.1230 0.07680 0.07499 -0.0919 0.9434 0.0295
-9.500 -0.0899 0.07348 0.07163 -0.0989 0.9353 0.0299
-9.250 -0.0545 0.06946 0.06754 -0.1078 0.9254 0.0305
-9.000 -0.3098 0.02026 0.01604 -0.1305 0.8489 0.0289
-8.500 -0.2773 0.01730 0.01270 -0.1277 0.8321 0.0297
-8.250 -0.2545 0.01683 0.01213 -0.1269 0.8243 0.0300
-8.000 -0.2309 0.01639 0.01162 -0.1261 0.8170 0.0304
-7.750 -0.2075 0.01592 0.01106 -0.1253 0.8092 0.0307
-7.500 -0.1838 0.01541 0.01045 -0.1245 0.8021 0.0311
-7.250 -0.1603 0.01483 0.00977 -0.1237 0.7942 0.0315
-7.000 -0.1364 0.01433 0.00914 -0.1229 0.7866 0.0319
-6.750 -0.1119 0.01385 0.00857 -0.1222 0.7786 0.0324
-6.250 -0.0620 0.01312 0.00762 -0.1208 0.7628 0.0331
-6.000 -0.0368 0.01285 0.00724 -0.1201 0.7546 0.0334
-5.750 -0.0141 0.01179 0.00611 -0.1192 0.7466 0.0340
-5.500 0.0107 0.01144 0.00571 -0.1185 0.7377 0.0345
-5.250 0.0365 0.01119 0.00543 -0.1179 0.7290 0.0350
-4.750 0.0876 0.01072 0.00486 -0.1166 0.7094 0.0361
-4.500 0.1130 0.01054 0.00461 -0.1159 0.6985 0.0367
-4.000 0.1633 0.01025 0.00416 -0.1144 0.6696 0.0379
-3.750 0.1884 0.01016 0.00398 -0.1136 0.6529 0.0383
-3.500 0.2113 0.00973 0.00348 -0.1125 0.6365 0.0392
-3.250 0.2360 0.00958 0.00327 -0.1117 0.6211 0.0400
-3.000 0.2611 0.00950 0.00314 -0.1110 0.6068 0.0409
-2.750 0.2863 0.00944 0.00301 -0.1103 0.5934 0.0418
-2.500 0.3114 0.00939 0.00289 -0.1096 0.5818 0.0428
-2.250 0.3375 0.00935 0.00280 -0.1090 0.5723 0.0437
-2.000 0.3623 0.00919 0.00259 -0.1083 0.5638 0.0452
-1.750 0.3883 0.00910 0.00248 -0.1077 0.5565 0.0468
-1.500 0.4138 0.00908 0.00241 -0.1071 0.5491 0.0483
-1.250 0.4406 0.00902 0.00234 -0.1067 0.5436 0.0499
-1.000 0.4666 0.00893 0.00222 -0.1061 0.5383 0.0520
-0.750 0.4922 0.00889 0.00216 -0.1055 0.5331 0.0548
-0.500 0.5191 0.00885 0.00211 -0.1052 0.5290 0.0577
-0.250 0.5455 0.00877 0.00205 -0.1047 0.5244 0.0628
0.000 0.5715 0.00872 0.00201 -0.1042 0.5201 0.0720
0.250 0.5949 0.00847 0.00202 -0.1033 0.5151 0.1659
0.500 0.6206 0.00829 0.00205 -0.1029 0.5116 0.2376
0.750 0.6462 0.00816 0.00208 -0.1023 0.5072 0.2949
1.000 0.6708 0.00805 0.00214 -0.1017 0.5027 0.3650
1.250 0.6930 0.00785 0.00223 -0.1005 0.4975 0.4876
1.500 0.7130 0.00740 0.00231 -0.0989 0.4933 0.6781
1.750 0.7992 0.00703 0.00256 -0.1115 0.4809 0.9881
2.000 0.8491 0.00713 0.00262 -0.1163 0.4729 1.0000
2.250 0.8717 0.00723 0.00267 -0.1151 0.4658 1.0000
2.500 0.8952 0.00731 0.00271 -0.1141 0.4593 1.0000
2.750 0.9181 0.00741 0.00277 -0.1130 0.4504 1.0000
3.000 0.9409 0.00752 0.00283 -0.1119 0.4399 1.0000
3.250 0.9626 0.00767 0.00290 -0.1105 0.4255 1.0000
3.500 0.9832 0.00787 0.00300 -0.1090 0.4049 1.0000
3.750 1.0013 0.00818 0.00315 -0.1071 0.3779 1.0000
4.000 1.0178 0.00857 0.00337 -0.1048 0.3498 1.0000
4.250 1.0358 0.00890 0.00358 -0.1029 0.3287 1.0000
4.500 1.0550 0.00919 0.00377 -0.1012 0.3148 1.0000
4.750 1.0747 0.00944 0.00396 -0.0996 0.3037 1.0000
5.000 1.0956 0.00965 0.00413 -0.0982 0.2954 1.0000
5.250 1.1151 0.00990 0.00432 -0.0966 0.2864 1.0000
5.500 1.1361 0.01009 0.00449 -0.0953 0.2792 1.0000
5.750 1.1552 0.01034 0.00470 -0.0936 0.2709 1.0000
6.000 1.1741 0.01054 0.00487 -0.0919 0.2642 1.0000
6.250 1.1913 0.01078 0.00507 -0.0898 0.2565 1.0000
6.500 1.2094 0.01101 0.00527 -0.0880 0.2497 1.0000
6.750 1.2274 0.01125 0.00549 -0.0862 0.2424 1.0000
7.000 1.2452 0.01152 0.00572 -0.0844 0.2356 1.0000
7.250 1.2638 0.01178 0.00596 -0.0827 0.2281 1.0000
7.500 1.2811 0.01210 0.00624 -0.0809 0.2207 1.0000
7.750 1.2997 0.01238 0.00650 -0.0794 0.2136 1.0000
8.000 1.3161 0.01276 0.00684 -0.0775 0.2040 1.0000
8.250 1.3321 0.01318 0.00720 -0.0756 0.1941 1.0000
8.500 1.3476 0.01363 0.00760 -0.0738 0.1827 1.0000
8.750 1.3621 0.01414 0.00805 -0.0718 0.1710 1.0000
9.000 1.3734 0.01483 0.00864 -0.0694 0.1548 1.0000
9.250 1.3804 0.01575 0.00942 -0.0666 0.1330 1.0000
9.500 1.3849 0.01687 0.01039 -0.0636 0.1097 1.0000
9.750 1.3742 0.01894 0.01219 -0.0590 0.0683 1.0000
10.000 1.3850 0.01987 0.01310 -0.0572 0.0623 1.0000
10.250 1.3987 0.02065 0.01390 -0.0558 0.0606 1.0000
10.500 1.4115 0.02152 0.01478 -0.0544 0.0589 1.0000
10.750 1.4237 0.02245 0.01574 -0.0530 0.0575 1.0000
11.000 1.4351 0.02346 0.01677 -0.0516 0.0558 1.0000
11.250 1.4472 0.02446 0.01780 -0.0504 0.0548 1.0000
11.500 1.4593 0.02546 0.01885 -0.0492 0.0540 1.0000
11.750 1.4726 0.02641 0.01984 -0.0483 0.0534 1.0000
12.000 1.4847 0.02747 0.02094 -0.0472 0.0529 1.0000
12.250 1.4961 0.02860 0.02213 -0.0462 0.0523 1.0000
12.500 1.5074 0.02976 0.02333 -0.0453 0.0520 1.0000
12.750 1.5165 0.03112 0.02474 -0.0443 0.0510 1.0000
13.000 1.5254 0.03253 0.02619 -0.0433 0.0503 1.0000
13.250 1.5332 0.03408 0.02779 -0.0424 0.0496 1.0000
13.500 1.5388 0.03585 0.02960 -0.0414 0.0485 1.0000
13.750 1.5439 0.03772 0.03153 -0.0406 0.0477 1.0000
14.000 1.5474 0.03982 0.03369 -0.0398 0.0469 1.0000
14.250 1.5558 0.04147 0.03540 -0.0393 0.0465 1.0000
14.500 1.5661 0.04295 0.03693 -0.0388 0.0461 1.0000
14.750 1.5757 0.04452 0.03855 -0.0384 0.0453 1.0000
15.000 1.5838 0.04626 0.04034 -0.0381 0.0442 1.0000
15.250 1.5900 0.04823 0.04234 -0.0377 0.0430 1.0000
15.500 1.5931 0.05058 0.04473 -0.0374 0.0419 1.0000
15.750 1.5929 0.05332 0.04751 -0.0371 0.0402 1.0000
16.000 1.6032 0.05491 0.04915 -0.0370 0.0386 1.0000
16.250 1.6056 0.05741 0.05165 -0.0368 0.0351 1.0000
16.500 1.6064 0.06014 0.05440 -0.0368 0.0313 1.0000
17.000 1.5641 0.07102 0.06530 -0.0371 0.0147 1.0000
17.500 1.5478 0.07912 0.07359 -0.0379 0.0133 1.0000
17.750 1.5395 0.08325 0.07781 -0.0384 0.0130 1.0000
18.000 1.5296 0.08766 0.08232 -0.0390 0.0127 1.0000
18.250 1.5182 0.09236 0.08712 -0.0398 0.0123 1.0000
18.500 1.5086 0.09684 0.09169 -0.0407 0.0122 1.0000
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