GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 500,000 Max Cl/Cd: 80.69 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe648-il-500000-n5.txt Download as CSV file: xf-goe648-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 648 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6917 0.10926 0.10606 -0.0533 1.0000 0.0198
-17.000 -0.7456 0.09593 0.09257 -0.0608 1.0000 0.0200
-16.750 -0.7947 0.08433 0.08081 -0.0675 1.0000 0.0200
-16.500 -0.8398 0.07405 0.07036 -0.0734 1.0000 0.0200
-16.250 -0.8809 0.06468 0.06083 -0.0789 1.0000 0.0200
-16.000 -0.9159 0.05631 0.05231 -0.0839 1.0000 0.0200
-15.750 -0.9411 0.04953 0.04537 -0.0880 1.0000 0.0201
-15.500 -0.9602 0.04402 0.03973 -0.0912 1.0000 0.0202
-15.250 -0.9756 0.03952 0.03510 -0.0933 1.0000 0.0203
-15.000 -0.9866 0.03609 0.03156 -0.0943 1.0000 0.0205
-14.750 -0.9957 0.03347 0.02884 -0.0941 1.0000 0.0207
-14.500 -1.0073 0.03133 0.02660 -0.0926 1.0000 0.0209
-14.250 -1.0232 0.02969 0.02487 -0.0893 1.0000 0.0210
-14.000 -1.0139 0.02834 0.02340 -0.0891 0.9981 0.0215
-13.750 -0.9953 0.02714 0.02208 -0.0898 0.9946 0.0219
-13.500 -0.9761 0.02607 0.02090 -0.0900 0.9910 0.0224
-13.250 -0.9550 0.02495 0.01974 -0.0904 0.9870 0.0229
-13.000 -0.9294 0.02402 0.01875 -0.0913 0.9840 0.0235
-12.750 -0.9018 0.02319 0.01785 -0.0924 0.9819 0.0242
-12.500 -0.8805 0.02247 0.01704 -0.0919 0.9773 0.0249
-12.250 -0.8553 0.02172 0.01620 -0.0922 0.9736 0.0255
-12.000 -0.8276 0.02095 0.01536 -0.0930 0.9709 0.0262
-11.750 -0.7984 0.02020 0.01458 -0.0940 0.9690 0.0269
-11.500 -0.7774 0.01961 0.01394 -0.0931 0.9625 0.0275
-11.250 -0.7479 0.01898 0.01324 -0.0938 0.9585 0.0283
-11.000 -0.7147 0.01836 0.01254 -0.0952 0.9556 0.0292
-10.750 -0.6916 0.01779 0.01192 -0.0945 0.9481 0.0299
-10.500 -0.6615 0.01719 0.01129 -0.0954 0.9437 0.0309
-10.250 -0.6276 0.01664 0.01070 -0.0968 0.9406 0.0318
-10.000 -0.6015 0.01620 0.01020 -0.0966 0.9336 0.0327
-9.750 -0.5705 0.01574 0.00967 -0.0974 0.9281 0.0336
-9.500 -0.5374 0.01518 0.00908 -0.0987 0.9236 0.0347
-9.250 -0.5116 0.01478 0.00866 -0.0983 0.9151 0.0357
-9.000 -0.4801 0.01438 0.00820 -0.0991 0.9088 0.0370
-8.750 -0.4520 0.01403 0.00779 -0.0991 0.9006 0.0381
-8.500 -0.4234 0.01363 0.00735 -0.0993 0.8923 0.0394
-8.250 -0.3963 0.01330 0.00699 -0.0991 0.8833 0.0407
-8.000 -0.3676 0.01301 0.00662 -0.0992 0.8727 0.0423
-7.750 -0.3421 0.01273 0.00628 -0.0986 0.8604 0.0438
-7.500 -0.3161 0.01247 0.00598 -0.0981 0.8490 0.0456
-7.250 -0.2901 0.01225 0.00569 -0.0975 0.8383 0.0477
-7.000 -0.2651 0.01203 0.00543 -0.0968 0.8273 0.0498
-6.750 -0.2396 0.01185 0.00519 -0.0961 0.8161 0.0523
-6.500 -0.2145 0.01168 0.00497 -0.0953 0.8052 0.0549
-6.250 -0.1893 0.01150 0.00477 -0.0946 0.7955 0.0578
-6.000 -0.1640 0.01137 0.00458 -0.0939 0.7843 0.0611
-5.750 -0.1391 0.01122 0.00439 -0.0931 0.7716 0.0642
-5.500 -0.1142 0.01110 0.00422 -0.0922 0.7583 0.0674
-5.250 -0.0891 0.01100 0.00404 -0.0914 0.7452 0.0702
-5.000 -0.0646 0.01085 0.00386 -0.0905 0.7310 0.0733
-4.750 -0.0400 0.01076 0.00371 -0.0896 0.7146 0.0766
-4.500 -0.0159 0.01071 0.00355 -0.0886 0.6953 0.0795
-4.250 0.0071 0.01062 0.00338 -0.0874 0.6741 0.0830
-3.750 0.0550 0.01054 0.00313 -0.0854 0.6380 0.0896
-3.500 0.0793 0.01045 0.00301 -0.0844 0.6231 0.0948
-3.000 0.1279 0.01033 0.00282 -0.0826 0.5956 0.1106
-2.500 0.1755 0.01015 0.00267 -0.0807 0.5662 0.1486
-2.250 0.1995 0.01008 0.00261 -0.0798 0.5510 0.1706
-2.000 0.2233 0.01000 0.00257 -0.0788 0.5371 0.1964
-1.750 0.2472 0.00995 0.00254 -0.0779 0.5229 0.2234
-1.500 0.2708 0.00991 0.00251 -0.0769 0.5077 0.2488
-1.250 0.2946 0.00989 0.00250 -0.0759 0.4912 0.2756
-1.000 0.3179 0.00989 0.00250 -0.0749 0.4728 0.3024
-0.750 0.3407 0.00991 0.00251 -0.0738 0.4506 0.3288
-0.500 0.3625 0.00996 0.00253 -0.0725 0.4241 0.3599
-0.250 0.3836 0.01000 0.00258 -0.0711 0.3984 0.4037
0.000 0.4047 0.01001 0.00266 -0.0697 0.3776 0.4575
0.250 0.4266 0.01005 0.00275 -0.0684 0.3621 0.5030
0.500 0.4489 0.01012 0.00284 -0.0672 0.3494 0.5388
0.750 0.4722 0.01018 0.00293 -0.0661 0.3397 0.5679
1.000 0.4946 0.01026 0.00302 -0.0649 0.3312 0.5972
1.250 0.5180 0.01028 0.00311 -0.0638 0.3250 0.6259
1.500 0.5400 0.01029 0.00321 -0.0625 0.3192 0.6636
1.750 0.5600 0.01029 0.00336 -0.0607 0.3136 0.7193
2.000 0.5816 0.01029 0.00347 -0.0592 0.3092 0.7651
2.250 0.6040 0.01033 0.00358 -0.0579 0.3045 0.7969
2.750 0.6501 0.01045 0.00384 -0.0556 0.2950 0.8664
3.000 0.7085 0.01060 0.00409 -0.0621 0.2904 0.9248
3.250 0.7860 0.01090 0.00436 -0.0728 0.2844 0.9803
3.500 0.8205 0.01116 0.00456 -0.0743 0.2799 1.0000
3.750 0.8405 0.01134 0.00469 -0.0727 0.2766 1.0000
4.000 0.8621 0.01146 0.00480 -0.0714 0.2742 1.0000
4.250 0.8834 0.01160 0.00493 -0.0700 0.2713 1.0000
4.500 0.9042 0.01175 0.00507 -0.0685 0.2679 1.0000
4.750 0.9245 0.01193 0.00522 -0.0670 0.2642 1.0000
5.000 0.9439 0.01214 0.00539 -0.0653 0.2608 1.0000
5.250 0.9635 0.01231 0.00555 -0.0637 0.2584 1.0000
5.500 0.9834 0.01245 0.00570 -0.0620 0.2556 1.0000
5.750 1.0029 0.01262 0.00586 -0.0604 0.2523 1.0000
6.000 1.0219 0.01281 0.00604 -0.0587 0.2488 1.0000
6.250 1.0404 0.01303 0.00624 -0.0569 0.2453 1.0000
6.500 1.0595 0.01325 0.00645 -0.0553 0.2423 1.0000
6.750 1.0803 0.01344 0.00665 -0.0539 0.2395 1.0000
7.000 1.1005 0.01364 0.00687 -0.0526 0.2363 1.0000
7.250 1.1200 0.01388 0.00710 -0.0511 0.2325 1.0000
7.500 1.1388 0.01416 0.00736 -0.0496 0.2288 1.0000
7.750 1.1585 0.01442 0.00762 -0.0482 0.2248 1.0000
8.000 1.1785 0.01467 0.00788 -0.0469 0.2198 1.0000
8.250 1.1967 0.01499 0.00818 -0.0454 0.2144 1.0000
8.500 1.2153 0.01532 0.00850 -0.0440 0.2105 1.0000
8.750 1.2350 0.01561 0.00882 -0.0428 0.2066 1.0000
9.000 1.2536 0.01595 0.00916 -0.0414 0.2023 1.0000
9.250 1.2705 0.01637 0.00957 -0.0399 0.1979 1.0000
9.500 1.2892 0.01674 0.00995 -0.0386 0.1940 1.0000
9.750 1.3070 0.01714 0.01037 -0.0373 0.1893 1.0000
10.000 1.3229 0.01765 0.01086 -0.0358 0.1843 1.0000
10.250 1.3400 0.01812 0.01134 -0.0345 0.1804 1.0000
10.500 1.3572 0.01859 0.01185 -0.0332 0.1765 1.0000
10.750 1.3730 0.01915 0.01241 -0.0318 0.1725 1.0000
11.000 1.3874 0.01980 0.01306 -0.0304 0.1688 1.0000
11.250 1.4042 0.02034 0.01364 -0.0292 0.1657 1.0000
11.500 1.4196 0.02097 0.01430 -0.0280 0.1618 1.0000
11.750 1.4335 0.02170 0.01505 -0.0267 0.1583 1.0000
12.000 1.4466 0.02251 0.01587 -0.0253 0.1548 1.0000
12.250 1.4618 0.02321 0.01662 -0.0242 0.1518 1.0000
12.500 1.4758 0.02400 0.01745 -0.0231 0.1488 1.0000
12.750 1.4879 0.02493 0.01841 -0.0219 0.1452 1.0000
13.000 1.4983 0.02600 0.01950 -0.0207 0.1418 1.0000
13.250 1.5118 0.02689 0.02045 -0.0198 0.1388 1.0000
13.500 1.5234 0.02794 0.02154 -0.0188 0.1351 1.0000
13.750 1.5324 0.02921 0.02283 -0.0177 0.1315 1.0000
14.000 1.5417 0.03049 0.02415 -0.0167 0.1284 1.0000
14.250 1.5522 0.03170 0.02543 -0.0159 0.1253 1.0000
14.500 1.5592 0.03323 0.02699 -0.0150 0.1206 1.0000
14.750 1.5643 0.03498 0.02877 -0.0141 0.1166 1.0000
15.000 1.5708 0.03664 0.03049 -0.0135 0.1118 1.0000
15.250 1.5710 0.03896 0.03281 -0.0127 0.1055 1.0000
15.500 1.5753 0.04097 0.03488 -0.0123 0.1011 1.0000
15.750 1.5728 0.04370 0.03763 -0.0118 0.0952 1.0000
16.000 1.5701 0.04655 0.04052 -0.0116 0.0880 1.0000
16.250 1.5638 0.04991 0.04392 -0.0115 0.0819 1.0000
16.500 1.5546 0.05370 0.04774 -0.0117 0.0760 1.0000
16.750 1.5409 0.05812 0.05220 -0.0121 0.0698 1.0000
17.000 1.5289 0.06250 0.05665 -0.0127 0.0665 1.0000
17.250 1.5146 0.06729 0.06151 -0.0136 0.0634 1.0000
17.500 1.4996 0.07228 0.06660 -0.0146 0.0616 1.0000
17.750 1.4848 0.07739 0.07181 -0.0158 0.0601 1.0000
18.000 1.4705 0.08253 0.07706 -0.0172 0.0588 1.0000
18.250 1.4543 0.08800 0.08264 -0.0188 0.0577 1.0000
18.500 1.4351 0.09402 0.08877 -0.0206 0.0564 1.0000
18.750 1.4182 0.09978 0.09464 -0.0225 0.0556 1.0000
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