GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 510 AIRFOIL (goe510-il) Reynolds number: 500,000 Max Cl/Cd: 84.79 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe510-il-500000.txt Download as CSV file: xf-goe510-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 510 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0738 0.08906 0.08659 -0.0922 0.9660 0.0421
-9.000 -0.0596 0.08623 0.08376 -0.0945 0.9622 0.0430
-8.750 -0.0437 0.08285 0.08037 -0.0984 0.9598 0.0440
-8.500 -0.0487 0.07306 0.07057 -0.1163 0.9560 0.0468
-8.250 -0.0613 0.06778 0.06528 -0.1186 0.9458 0.0471
-8.000 -0.0420 0.06497 0.06246 -0.1202 0.9439 0.0474
-7.750 -0.0189 0.06234 0.05982 -0.1231 0.9421 0.0478
-7.500 -0.0120 0.06024 0.05771 -0.1227 0.9335 0.0481
-7.250 0.0101 0.05751 0.05494 -0.1260 0.9296 0.0488
-7.000 0.0375 0.05412 0.05150 -0.1313 0.9268 0.0499
-6.750 0.0118 0.03988 0.03678 -0.1386 0.9112 0.0548
-6.500 0.0234 0.03894 0.03584 -0.1364 0.9007 0.0551
-6.250 0.0528 0.03775 0.03461 -0.1381 0.8955 0.0556
-6.000 0.0662 0.03663 0.03343 -0.1364 0.8846 0.0561
-5.750 0.0895 0.03471 0.03140 -0.1374 0.8768 0.0571
-5.500 0.0985 0.03090 0.02733 -0.1362 0.8655 0.0595
-5.250 0.0710 0.02190 0.01713 -0.1284 0.8515 0.0522
-5.000 0.0869 0.01964 0.01452 -0.1264 0.8420 0.0509
-4.750 0.1076 0.01818 0.01275 -0.1251 0.8322 0.0508
-4.500 0.1273 0.01715 0.01150 -0.1234 0.8216 0.0510
-4.250 0.1522 0.01629 0.01041 -0.1228 0.8116 0.0514
-4.000 0.1736 0.01561 0.00955 -0.1213 0.7999 0.0520
-3.750 0.1959 0.01515 0.00893 -0.1200 0.7885 0.0528
-3.500 0.2202 0.01483 0.00843 -0.1190 0.7775 0.0535
-3.250 0.2420 0.01450 0.00797 -0.1175 0.7652 0.0539
-3.000 0.2636 0.01388 0.00721 -0.1161 0.7527 0.0543
-2.750 0.2860 0.01303 0.00627 -0.1149 0.7397 0.0552
-2.500 0.3081 0.01262 0.00580 -0.1136 0.7262 0.0561
-2.250 0.3295 0.01235 0.00545 -0.1121 0.7123 0.0569
-2.000 0.3503 0.01213 0.00518 -0.1105 0.6984 0.0580
-1.750 0.3712 0.01196 0.00494 -0.1089 0.6847 0.0593
-1.500 0.3917 0.01181 0.00471 -0.1072 0.6710 0.0604
-1.250 0.4118 0.01168 0.00449 -0.1054 0.6576 0.0612
-1.000 0.4318 0.01160 0.00432 -0.1036 0.6445 0.0620
-0.750 0.4512 0.01143 0.00410 -0.1017 0.6316 0.0629
-0.500 0.4692 0.01117 0.00380 -0.0995 0.6191 0.0645
-0.250 0.4864 0.01109 0.00367 -0.0971 0.6058 0.0659
0.000 0.5022 0.01104 0.00357 -0.0945 0.5922 0.0680
0.250 0.5181 0.01099 0.00348 -0.0918 0.5779 0.0696
0.500 0.5337 0.01097 0.00340 -0.0891 0.5625 0.0710
0.750 0.5492 0.01100 0.00335 -0.0864 0.5462 0.0723
1.000 0.5634 0.01098 0.00327 -0.0834 0.5292 0.0754
1.250 0.5786 0.01104 0.00326 -0.0807 0.5126 0.0788
1.500 0.5949 0.01113 0.00328 -0.0783 0.4976 0.0833
1.750 0.6105 0.01116 0.00333 -0.0757 0.4846 0.1029
2.000 0.6239 0.01109 0.00352 -0.0728 0.4736 0.2105
2.250 0.6431 0.01120 0.00367 -0.0711 0.4640 0.2471
2.750 0.6827 0.01149 0.00395 -0.0678 0.4482 0.2833
3.000 0.7023 0.01166 0.00408 -0.0662 0.4413 0.2975
3.250 0.7227 0.01180 0.00422 -0.0648 0.4355 0.3120
3.500 0.7435 0.01190 0.00434 -0.0634 0.4298 0.3237
3.750 0.7628 0.01205 0.00448 -0.0617 0.4241 0.3366
4.000 0.7829 0.01218 0.00462 -0.0602 0.4190 0.3526
4.250 0.8030 0.01221 0.00475 -0.0588 0.4143 0.3787
4.500 0.8068 0.01163 0.00485 -0.0540 0.4104 0.6739
4.750 1.0121 0.01222 0.00609 -0.0926 0.3974 0.9971
5.000 1.0564 0.01248 0.00630 -0.0964 0.3917 1.0000
5.250 1.0690 0.01270 0.00645 -0.0935 0.3875 1.0000
5.500 1.0831 0.01282 0.00659 -0.0908 0.3838 1.0000
5.750 1.0972 0.01294 0.00672 -0.0882 0.3798 1.0000
6.000 1.1104 0.01310 0.00687 -0.0854 0.3755 1.0000
6.250 1.1234 0.01333 0.00705 -0.0826 0.3710 1.0000
6.500 1.1386 0.01350 0.00723 -0.0802 0.3671 1.0000
6.750 1.1541 0.01365 0.00740 -0.0779 0.3630 1.0000
7.000 1.1687 0.01385 0.00760 -0.0755 0.3585 1.0000
7.500 1.1982 0.01429 0.00803 -0.0708 0.3477 1.0000
7.750 1.2124 0.01452 0.00825 -0.0685 0.3413 1.0000
8.000 1.2265 0.01486 0.00855 -0.0661 0.3359 1.0000
8.250 1.2438 0.01505 0.00879 -0.0644 0.3296 1.0000
8.500 1.2568 0.01540 0.00909 -0.0620 0.3218 1.0000
8.750 1.2731 0.01568 0.00939 -0.0602 0.3141 1.0000
9.000 1.2869 0.01608 0.00976 -0.0580 0.3062 1.0000
9.250 1.3028 0.01643 0.01013 -0.0563 0.2986 1.0000
9.500 1.3169 0.01688 0.01055 -0.0543 0.2906 1.0000
9.750 1.3322 0.01730 0.01098 -0.0525 0.2829 1.0000
10.000 1.3453 0.01784 0.01149 -0.0505 0.2746 1.0000
10.250 1.3596 0.01835 0.01200 -0.0487 0.2650 1.0000
10.500 1.3708 0.01903 0.01264 -0.0466 0.2556 1.0000
10.750 1.3826 0.01971 0.01329 -0.0446 0.2443 1.0000
11.000 1.3931 0.02049 0.01404 -0.0426 0.2317 1.0000
11.250 1.4019 0.02139 0.01489 -0.0404 0.2185 1.0000
11.500 1.4086 0.02246 0.01589 -0.0381 0.2030 1.0000
11.750 1.4099 0.02390 0.01720 -0.0353 0.1828 1.0000
12.000 1.4062 0.02575 0.01888 -0.0322 0.1549 1.0000
12.250 1.3961 0.02813 0.02106 -0.0288 0.1241 1.0000
12.500 1.3798 0.03115 0.02389 -0.0253 0.0943 1.0000
12.750 1.3633 0.03441 0.02700 -0.0223 0.0674 1.0000
13.000 1.3387 0.03866 0.03112 -0.0193 0.0324 1.0000
13.250 1.3332 0.04148 0.03399 -0.0179 0.0268 1.0000
13.500 1.3319 0.04403 0.03662 -0.0168 0.0247 1.0000
13.750 1.3328 0.04646 0.03913 -0.0160 0.0238 1.0000
14.000 1.3317 0.04916 0.04193 -0.0152 0.0227 1.0000
14.250 1.3318 0.05180 0.04468 -0.0147 0.0221 1.0000
14.500 1.3306 0.05465 0.04762 -0.0142 0.0215 1.0000
14.750 1.3288 0.05763 0.05071 -0.0139 0.0211 1.0000
15.000 1.3226 0.06122 0.05441 -0.0137 0.0206 1.0000
15.250 1.3151 0.06505 0.05834 -0.0137 0.0201 1.0000
15.500 1.3039 0.06945 0.06286 -0.0139 0.0197 1.0000
15.750 1.2940 0.07381 0.06734 -0.0142 0.0195 1.0000
16.000 1.2873 0.07783 0.07146 -0.0146 0.0192 1.0000
16.250 1.2801 0.08198 0.07571 -0.0152 0.0189 1.0000
16.500 1.2723 0.08624 0.08007 -0.0158 0.0187 1.0000
16.750 1.2635 0.09071 0.08465 -0.0166 0.0185 1.0000
17.000 1.2548 0.09523 0.08927 -0.0174 0.0182 1.0000
17.250 1.2455 0.09983 0.09397 -0.0184 0.0179 1.0000
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