GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 615 AIRFOIL (goe615-il) Reynolds number: 500,000 Max Cl/Cd: 104.09 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe615-il-500000.txt Download as CSV file: xf-goe615-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1736 0.08992 0.08759 -0.0768 0.9732 0.0383
-9.750 -0.1575 0.08616 0.08383 -0.0786 0.9698 0.0387
-9.500 -0.1406 0.08378 0.08145 -0.0799 0.9617 0.0390
-9.250 -0.1185 0.08110 0.07876 -0.0829 0.9570 0.0394
-9.000 -0.0982 0.07796 0.07560 -0.0868 0.9498 0.0401
-8.750 -0.0981 0.06167 0.05924 -0.1143 0.9339 0.0442
-8.500 -0.0704 0.05989 0.05743 -0.1162 0.9264 0.0445
-8.250 -0.0475 0.05794 0.05542 -0.1189 0.9140 0.0450
-8.000 -0.0345 0.05535 0.05277 -0.1219 0.8986 0.0454
-7.750 -0.0281 0.05205 0.04937 -0.1249 0.8830 0.0460
-7.500 -0.0773 0.03991 0.03640 -0.1320 0.8598 0.0505
-7.250 -0.0786 0.03473 0.03104 -0.1313 0.8495 0.0512
-7.000 -0.0584 0.03341 0.02973 -0.1309 0.8412 0.0518
-6.750 -0.0715 0.02539 0.02075 -0.1275 0.8305 0.0434
-6.500 -0.0555 0.02299 0.01808 -0.1263 0.8227 0.0428
-6.250 -0.0386 0.02114 0.01594 -0.1248 0.8139 0.0427
-6.000 -0.0179 0.01981 0.01430 -0.1236 0.8059 0.0432
-5.750 0.0029 0.01857 0.01282 -0.1224 0.7970 0.0432
-5.500 0.0260 0.01759 0.01159 -0.1214 0.7886 0.0435
-5.250 0.0494 0.01685 0.01066 -0.1204 0.7797 0.0438
-5.000 0.0735 0.01603 0.00962 -0.1196 0.7712 0.0442
-4.750 0.0969 0.01482 0.00834 -0.1188 0.7619 0.0447
-4.500 0.1220 0.01425 0.00771 -0.1181 0.7530 0.0456
-4.250 0.1469 0.01383 0.00726 -0.1174 0.7425 0.0465
-4.000 0.1721 0.01341 0.00675 -0.1167 0.7326 0.0473
-3.750 0.1971 0.01300 0.00626 -0.1159 0.7215 0.0481
-3.500 0.2220 0.01263 0.00581 -0.1151 0.7094 0.0489
-3.250 0.2469 0.01234 0.00542 -0.1142 0.6964 0.0497
-3.000 0.2717 0.01217 0.00513 -0.1133 0.6825 0.0504
-2.750 0.2947 0.01160 0.00452 -0.1122 0.6689 0.0519
-2.500 0.3189 0.01135 0.00425 -0.1114 0.6556 0.0534
-2.250 0.3436 0.01117 0.00402 -0.1105 0.6434 0.0549
-2.000 0.3680 0.01103 0.00379 -0.1097 0.6318 0.0564
-1.750 0.3930 0.01092 0.00362 -0.1089 0.6207 0.0579
-1.500 0.4171 0.01065 0.00331 -0.1080 0.6112 0.0603
-1.250 0.4418 0.01055 0.00316 -0.1072 0.6018 0.0631
-1.000 0.4674 0.01048 0.00305 -0.1066 0.5933 0.0664
-0.750 0.4923 0.01036 0.00291 -0.1058 0.5858 0.0712
-0.500 0.5181 0.01029 0.00283 -0.1053 0.5794 0.0778
-0.250 0.5432 0.01014 0.00277 -0.1046 0.5730 0.1046
0.000 0.5657 0.00975 0.00280 -0.1037 0.5671 0.2531
0.250 0.5904 0.00957 0.00285 -0.1030 0.5618 0.3286
0.500 0.6138 0.00935 0.00291 -0.1022 0.5559 0.4315
0.750 0.6324 0.00892 0.00302 -0.1003 0.5507 0.6275
1.000 0.7322 0.00839 0.00328 -0.1154 0.5430 0.9966
1.250 0.7643 0.00851 0.00331 -0.1162 0.5369 1.0000
1.500 0.7873 0.00866 0.00337 -0.1151 0.5314 1.0000
1.750 0.8108 0.00873 0.00343 -0.1141 0.5261 1.0000
2.000 0.8338 0.00884 0.00348 -0.1130 0.5200 1.0000
2.250 0.8563 0.00899 0.00355 -0.1119 0.5132 1.0000
2.500 0.8793 0.00907 0.00362 -0.1108 0.5061 1.0000
2.750 0.9011 0.00923 0.00369 -0.1094 0.4980 1.0000
3.000 0.9237 0.00930 0.00376 -0.1083 0.4893 1.0000
3.250 0.9455 0.00945 0.00384 -0.1070 0.4814 1.0000
3.500 0.9683 0.00953 0.00392 -0.1059 0.4730 1.0000
3.750 0.9893 0.00969 0.00401 -0.1044 0.4638 1.0000
4.000 1.0116 0.00979 0.00410 -0.1032 0.4528 1.0000
4.250 1.0325 0.00993 0.00420 -0.1018 0.4404 1.0000
4.500 1.0523 0.01011 0.00432 -0.1001 0.4243 1.0000
4.750 1.0703 0.01034 0.00446 -0.0982 0.4034 1.0000
5.000 1.0855 0.01068 0.00465 -0.0958 0.3788 1.0000
5.250 1.1005 0.01107 0.00490 -0.0933 0.3574 1.0000
5.500 1.1152 0.01146 0.00518 -0.0909 0.3402 1.0000
5.750 1.1293 0.01182 0.00546 -0.0883 0.3270 1.0000
6.000 1.1435 0.01219 0.00575 -0.0857 0.3163 1.0000
6.250 1.1602 0.01250 0.00603 -0.0837 0.3071 1.0000
6.500 1.1761 0.01284 0.00634 -0.0816 0.2991 1.0000
6.750 1.1937 0.01315 0.00663 -0.0798 0.2914 1.0000
7.000 1.2094 0.01354 0.00697 -0.0777 0.2840 1.0000
7.250 1.2280 0.01383 0.00726 -0.0762 0.2769 1.0000
7.500 1.2433 0.01425 0.00764 -0.0741 0.2698 1.0000
7.750 1.2620 0.01455 0.00796 -0.0727 0.2635 1.0000
8.000 1.2785 0.01495 0.00835 -0.0710 0.2569 1.0000
8.250 1.2949 0.01537 0.00876 -0.0693 0.2510 1.0000
8.500 1.3121 0.01576 0.00915 -0.0678 0.2435 1.0000
8.750 1.3263 0.01630 0.00965 -0.0659 0.2373 1.0000
9.000 1.3444 0.01668 0.01007 -0.0646 0.2313 1.0000
9.250 1.3590 0.01723 0.01061 -0.0628 0.2244 1.0000
9.500 1.3750 0.01774 0.01113 -0.0614 0.2186 1.0000
9.750 1.3897 0.01833 0.01171 -0.0598 0.2112 1.0000
10.000 1.4036 0.01898 0.01237 -0.0582 0.2043 1.0000
10.250 1.4166 0.01971 0.01307 -0.0566 0.1950 1.0000
10.500 1.4287 0.02051 0.01385 -0.0549 0.1844 1.0000
10.750 1.4388 0.02147 0.01477 -0.0532 0.1730 1.0000
11.000 1.4476 0.02255 0.01580 -0.0514 0.1608 1.0000
11.250 1.4557 0.02372 0.01693 -0.0496 0.1491 1.0000
11.500 1.4601 0.02519 0.01832 -0.0477 0.1318 1.0000
11.750 1.4555 0.02738 0.02034 -0.0452 0.1058 1.0000
12.000 1.4476 0.02993 0.02274 -0.0428 0.0820 1.0000
12.250 1.4476 0.03199 0.02477 -0.0411 0.0742 1.0000
12.500 1.4528 0.03371 0.02651 -0.0399 0.0708 1.0000
12.750 1.4567 0.03558 0.02843 -0.0388 0.0683 1.0000
13.000 1.4609 0.03749 0.03038 -0.0378 0.0666 1.0000
13.250 1.4645 0.03952 0.03246 -0.0369 0.0652 1.0000
13.500 1.4661 0.04182 0.03481 -0.0361 0.0635 1.0000
13.750 1.4685 0.04408 0.03715 -0.0354 0.0626 1.0000
14.000 1.4728 0.04622 0.03937 -0.0349 0.0617 1.0000
14.250 1.4770 0.04841 0.04165 -0.0344 0.0612 1.0000
14.500 1.4800 0.05079 0.04411 -0.0341 0.0604 1.0000
14.750 1.4821 0.05329 0.04670 -0.0338 0.0597 1.0000
15.000 1.4824 0.05605 0.04954 -0.0336 0.0590 1.0000
15.250 1.4828 0.05885 0.05243 -0.0335 0.0584 1.0000
15.500 1.4798 0.06210 0.05575 -0.0335 0.0575 1.0000
15.750 1.4758 0.06549 0.05922 -0.0336 0.0567 1.0000
16.000 1.4709 0.06905 0.06285 -0.0337 0.0558 1.0000
16.250 1.4626 0.07309 0.06697 -0.0340 0.0548 1.0000
16.500 1.4554 0.07705 0.07102 -0.0344 0.0541 1.0000
16.750 1.4581 0.07976 0.07382 -0.0347 0.0536 1.0000
17.000 1.4586 0.08280 0.07696 -0.0351 0.0529 1.0000
17.250 1.4578 0.08604 0.08029 -0.0356 0.0521 1.0000
17.500 1.4558 0.08948 0.08382 -0.0362 0.0513 1.0000
17.750 1.4528 0.09311 0.08754 -0.0370 0.0504 1.0000
18.000 1.4472 0.09712 0.09163 -0.0378 0.0495 1.0000
18.250 1.4398 0.10146 0.09603 -0.0389 0.0484 1.0000
18.500 1.4304 0.10616 0.10081 -0.0402 0.0475 1.0000
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