GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 500,000 Max Cl/Cd: 72.15 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe617-il-500000-n5.txt Download as CSV file: xf-goe617-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 617 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9317 0.08815 0.08485 -0.0534 1.0000 0.0167
-17.250 -0.9975 0.07272 0.06914 -0.0626 1.0000 0.0166
-17.000 -1.0373 0.06220 0.05840 -0.0693 1.0000 0.0165
-16.750 -1.0645 0.05434 0.05034 -0.0743 1.0000 0.0165
-16.500 -1.0795 0.04883 0.04469 -0.0776 1.0000 0.0167
-16.250 -1.0903 0.04445 0.04017 -0.0798 1.0000 0.0168
-16.000 -1.0953 0.04120 0.03681 -0.0808 1.0000 0.0172
-15.750 -1.1018 0.03816 0.03364 -0.0811 1.0000 0.0172
-15.500 -1.1015 0.03607 0.03146 -0.0807 1.0000 0.0177
-15.250 -1.1024 0.03407 0.02936 -0.0798 1.0000 0.0180
-15.000 -1.1001 0.03250 0.02767 -0.0785 1.0000 0.0184
-14.750 -1.0980 0.03103 0.02608 -0.0768 1.0000 0.0189
-14.500 -1.0945 0.02977 0.02471 -0.0749 1.0000 0.0193
-14.250 -1.0910 0.02861 0.02343 -0.0726 1.0000 0.0196
-14.000 -1.0885 0.02750 0.02225 -0.0699 1.0000 0.0199
-13.750 -1.0828 0.02669 0.02141 -0.0674 1.0000 0.0205
-13.500 -1.0782 0.02590 0.02056 -0.0644 1.0000 0.0209
-13.250 -1.0737 0.02519 0.01978 -0.0611 1.0000 0.0212
-13.000 -1.0669 0.02468 0.01921 -0.0580 1.0000 0.0219
-12.750 -1.0648 0.02410 0.01856 -0.0540 1.0000 0.0223
-12.500 -1.0642 0.02365 0.01803 -0.0494 1.0000 0.0228
-12.000 -1.0338 0.02244 0.01664 -0.0460 0.9971 0.0238
-11.750 -1.0077 0.02162 0.01578 -0.0467 0.9937 0.0246
-11.500 -0.9816 0.02104 0.01516 -0.0470 0.9901 0.0255
-11.250 -0.9544 0.02042 0.01448 -0.0475 0.9866 0.0263
-11.000 -0.9254 0.01984 0.01381 -0.0483 0.9838 0.0271
-10.750 -0.9002 0.01927 0.01316 -0.0483 0.9790 0.0278
-10.500 -0.8735 0.01864 0.01246 -0.0486 0.9748 0.0286
-10.250 -0.8449 0.01798 0.01178 -0.0493 0.9718 0.0295
-10.000 -0.8197 0.01749 0.01125 -0.0491 0.9648 0.0304
-9.750 -0.7881 0.01697 0.01068 -0.0503 0.9602 0.0315
-9.500 -0.7575 0.01648 0.01011 -0.0511 0.9545 0.0324
-9.250 -0.7257 0.01603 0.00958 -0.0522 0.9494 0.0333
-9.000 -0.6932 0.01540 0.00894 -0.0536 0.9451 0.0345
-8.750 -0.6627 0.01494 0.00845 -0.0545 0.9389 0.0357
-8.500 -0.6308 0.01451 0.00798 -0.0556 0.9328 0.0369
-8.250 -0.5974 0.01409 0.00750 -0.0570 0.9273 0.0382
-8.000 -0.5690 0.01374 0.00709 -0.0573 0.9190 0.0394
-7.750 -0.5390 0.01333 0.00664 -0.0579 0.9121 0.0410
-7.500 -0.5134 0.01303 0.00632 -0.0576 0.9036 0.0427
-7.250 -0.4857 0.01275 0.00599 -0.0576 0.8960 0.0447
-7.000 -0.4614 0.01250 0.00570 -0.0569 0.8878 0.0467
-6.750 -0.4358 0.01226 0.00545 -0.0565 0.8800 0.0493
-6.500 -0.4116 0.01206 0.00522 -0.0557 0.8719 0.0520
-6.250 -0.3868 0.01187 0.00498 -0.0551 0.8639 0.0547
-6.000 -0.3627 0.01168 0.00478 -0.0543 0.8561 0.0578
-5.750 -0.3379 0.01154 0.00459 -0.0536 0.8479 0.0610
-5.500 -0.3135 0.01139 0.00440 -0.0528 0.8397 0.0636
-5.250 -0.2897 0.01120 0.00419 -0.0520 0.8310 0.0669
-5.000 -0.2653 0.01105 0.00402 -0.0512 0.8228 0.0699
-4.750 -0.2407 0.01094 0.00384 -0.0504 0.8135 0.0723
-4.500 -0.2165 0.01079 0.00366 -0.0496 0.8044 0.0745
-4.250 -0.1928 0.01062 0.00345 -0.0486 0.7948 0.0775
-4.000 -0.1690 0.01047 0.00328 -0.0477 0.7839 0.0804
-3.750 -0.1448 0.01035 0.00312 -0.0469 0.7731 0.0834
-3.500 -0.1206 0.01027 0.00296 -0.0460 0.7610 0.0860
-3.250 -0.0973 0.01012 0.00280 -0.0450 0.7472 0.0916
-3.000 -0.0742 0.01000 0.00266 -0.0439 0.7313 0.0985
-2.750 -0.0520 0.00985 0.00252 -0.0427 0.7137 0.1143
-2.250 -0.0083 0.00954 0.00233 -0.0401 0.6802 0.1811
-2.000 0.0149 0.00947 0.00225 -0.0391 0.6652 0.1984
-1.750 0.0382 0.00939 0.00217 -0.0381 0.6514 0.2152
-1.250 0.0793 0.00890 0.00200 -0.0352 0.6281 0.3298
-1.000 0.0994 0.00866 0.00196 -0.0336 0.6164 0.4023
-0.750 0.1203 0.00849 0.00192 -0.0321 0.6054 0.4525
-0.500 0.1409 0.00835 0.00190 -0.0306 0.5954 0.4985
-0.250 0.1606 0.00815 0.00188 -0.0289 0.5860 0.5569
0.000 0.1786 0.00795 0.00187 -0.0267 0.5767 0.6201
0.250 0.1964 0.00778 0.00187 -0.0244 0.5649 0.6799
0.500 0.2151 0.00762 0.00190 -0.0223 0.5530 0.7392
0.750 0.2367 0.00753 0.00199 -0.0207 0.5409 0.8041
1.000 0.2656 0.00757 0.00212 -0.0207 0.5308 0.8504
1.250 0.2963 0.00764 0.00222 -0.0212 0.5218 0.8762
1.500 0.3272 0.00777 0.00233 -0.0217 0.5127 0.8940
1.750 0.3621 0.00789 0.00244 -0.0232 0.5024 0.9052
2.000 0.3938 0.00804 0.00255 -0.0239 0.4897 0.9145
2.250 0.4238 0.00822 0.00267 -0.0243 0.4762 0.9248
2.500 0.4613 0.00842 0.00283 -0.0264 0.4646 0.9324
2.750 0.4918 0.00856 0.00294 -0.0269 0.4543 0.9380
3.000 0.5193 0.00872 0.00305 -0.0268 0.4441 0.9441
3.500 0.5864 0.00922 0.00344 -0.0292 0.4142 0.9559
3.750 0.6196 0.00950 0.00363 -0.0304 0.3939 0.9597
4.000 0.6542 0.00979 0.00383 -0.0320 0.3729 0.9625
4.250 0.6847 0.01005 0.00401 -0.0327 0.3555 0.9661
4.500 0.7072 0.01030 0.00419 -0.0317 0.3387 0.9713
4.750 0.7390 0.01056 0.00437 -0.0328 0.3210 0.9727
5.000 0.7694 0.01084 0.00457 -0.0336 0.3026 0.9746
5.250 0.7981 0.01111 0.00477 -0.0340 0.2842 0.9770
5.500 0.8240 0.01142 0.00499 -0.0339 0.2615 0.9800
5.750 0.8461 0.01186 0.00527 -0.0331 0.2279 0.9834
6.000 0.8722 0.01247 0.00564 -0.0334 0.1863 0.9853
6.250 0.8994 0.01287 0.00596 -0.0337 0.1708 0.9874
6.500 0.9265 0.01320 0.00625 -0.0340 0.1614 0.9897
6.750 0.9526 0.01353 0.00656 -0.0340 0.1535 0.9921
7.000 0.9790 0.01383 0.00686 -0.0341 0.1470 0.9941
7.250 1.0074 0.01413 0.00715 -0.0346 0.1394 0.9958
7.500 1.0353 0.01446 0.00746 -0.0351 0.1318 0.9978
7.750 1.0627 0.01480 0.00779 -0.0355 0.1231 0.9995
8.000 1.0802 0.01510 0.00808 -0.0338 0.1168 1.0000
8.250 1.0899 0.01539 0.00836 -0.0305 0.1103 1.0000
8.500 1.0955 0.01567 0.00863 -0.0264 0.1052 1.0000
8.750 1.1000 0.01592 0.00889 -0.0220 0.1006 1.0000
9.000 1.1048 0.01624 0.00921 -0.0178 0.0963 1.0000
9.250 1.1118 0.01658 0.00956 -0.0141 0.0927 1.0000
9.500 1.1199 0.01695 0.00994 -0.0107 0.0887 1.0000
9.750 1.1276 0.01741 0.01039 -0.0074 0.0849 1.0000
10.000 1.1368 0.01788 0.01087 -0.0044 0.0814 1.0000
10.250 1.1476 0.01833 0.01136 -0.0018 0.0786 1.0000
10.500 1.1578 0.01885 0.01190 0.0008 0.0760 1.0000
10.750 1.1672 0.01946 0.01252 0.0033 0.0735 1.0000
11.000 1.1765 0.02012 0.01321 0.0058 0.0711 1.0000
11.250 1.1889 0.02068 0.01382 0.0077 0.0696 1.0000
11.500 1.2006 0.02131 0.01451 0.0096 0.0679 1.0000
11.750 1.2116 0.02203 0.01526 0.0115 0.0657 1.0000
12.000 1.2214 0.02285 0.01611 0.0134 0.0634 1.0000
12.250 1.2304 0.02377 0.01706 0.0152 0.0615 1.0000
12.500 1.2418 0.02459 0.01793 0.0167 0.0598 1.0000
12.750 1.2528 0.02547 0.01888 0.0182 0.0585 1.0000
13.000 1.2630 0.02645 0.01990 0.0196 0.0561 1.0000
13.250 1.2715 0.02757 0.02105 0.0209 0.0535 1.0000
13.500 1.2801 0.02876 0.02227 0.0222 0.0514 1.0000
13.750 1.2895 0.02992 0.02350 0.0233 0.0494 1.0000
14.000 1.2977 0.03121 0.02485 0.0243 0.0467 1.0000
14.250 1.3038 0.03273 0.02638 0.0253 0.0439 1.0000
14.500 1.3109 0.03421 0.02793 0.0262 0.0406 1.0000
14.750 1.3151 0.03602 0.02975 0.0270 0.0363 1.0000
15.000 1.3167 0.03811 0.03184 0.0278 0.0303 1.0000
15.250 1.3120 0.04088 0.03459 0.0284 0.0227 1.0000
15.500 1.3084 0.04369 0.03743 0.0288 0.0194 1.0000
15.750 1.3081 0.04626 0.04006 0.0291 0.0180 1.0000
16.000 1.3049 0.04923 0.04311 0.0291 0.0166 1.0000
16.250 1.3023 0.05224 0.04620 0.0290 0.0156 1.0000
16.500 1.3012 0.05515 0.04919 0.0288 0.0150 1.0000
16.750 1.2991 0.05823 0.05237 0.0284 0.0145 1.0000
17.000 1.2959 0.06154 0.05578 0.0278 0.0141 1.0000
17.250 1.2897 0.06530 0.05964 0.0271 0.0135 1.0000
17.500 1.2833 0.06917 0.06360 0.0262 0.0131 1.0000
17.750 1.2762 0.07324 0.06777 0.0251 0.0129 1.0000
18.000 1.2686 0.07749 0.07213 0.0238 0.0127 1.0000
18.250 1.2618 0.08170 0.07645 0.0225 0.0123 1.0000
18.500 1.2532 0.08624 0.08110 0.0210 0.0122 1.0000
18.750 1.2444 0.09090 0.08588 0.0193 0.0120 1.0000
19.000 1.2346 0.09581 0.09091 0.0175 0.0118 1.0000
19.250 1.2231 0.10102 0.09623 0.0154 0.0114 1.0000
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