GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 500,000 Max Cl/Cd: 83.64 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe512-il-500000.txt Download as CSV file: xf-goe512-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1199 0.10489 0.10273 -0.0651 0.9833 0.0295
-11.000 -0.5712 0.04526 0.04250 -0.0925 0.9746 0.0192
-10.750 -0.5942 0.03720 0.03384 -0.0938 0.9666 0.0193
-10.500 -0.5915 0.03389 0.03028 -0.0927 0.9608 0.0196
-10.250 -0.5739 0.03141 0.02758 -0.0931 0.9583 0.0199
-10.000 -0.5428 0.03051 0.02662 -0.0947 0.9569 0.0204
-9.750 -0.5400 0.02885 0.02476 -0.0909 0.9484 0.0207
-9.500 -0.5161 0.02719 0.02288 -0.0912 0.9455 0.0214
-9.250 -0.4917 0.02516 0.02052 -0.0916 0.9435 0.0220
-9.000 -0.4625 0.02353 0.01855 -0.0924 0.9422 0.0227
-8.750 -0.4590 0.02224 0.01710 -0.0879 0.9331 0.0233
-8.500 -0.4281 0.02138 0.01622 -0.0888 0.9309 0.0241
-8.250 -0.3939 0.02073 0.01551 -0.0902 0.9294 0.0252
-8.000 -0.3598 0.01975 0.01435 -0.0915 0.9283 0.0263
-7.750 -0.3252 0.01855 0.01292 -0.0929 0.9272 0.0274
-7.500 -0.3167 0.01781 0.01216 -0.0889 0.9182 0.0282
-7.250 -0.2831 0.01718 0.01151 -0.0900 0.9159 0.0294
-7.000 -0.2458 0.01656 0.01078 -0.0918 0.9140 0.0311
-6.750 -0.2063 0.01559 0.00970 -0.0942 0.9123 0.0330
-6.500 -0.1926 0.01521 0.00933 -0.0910 0.9030 0.0341
-6.250 -0.1558 0.01470 0.00876 -0.0927 0.8992 0.0362
-6.000 -0.1174 0.01401 0.00796 -0.0948 0.8963 0.0382
-5.750 -0.1011 0.01357 0.00753 -0.0922 0.8863 0.0399
-5.500 -0.0622 0.01320 0.00712 -0.0943 0.8816 0.0426
-5.250 -0.0382 0.01296 0.00679 -0.0932 0.8714 0.0443
-5.000 -0.0020 0.01223 0.00606 -0.0949 0.8639 0.0474
-4.750 0.0261 0.01199 0.00577 -0.0948 0.8522 0.0502
-4.500 0.0553 0.01172 0.00541 -0.0948 0.8403 0.0525
-4.250 0.0841 0.01126 0.00493 -0.0949 0.8281 0.0562
-4.000 0.1134 0.01107 0.00465 -0.0950 0.8146 0.0596
-3.750 0.1390 0.01081 0.00430 -0.0943 0.7989 0.0628
-3.500 0.1624 0.01058 0.00402 -0.0932 0.7823 0.0674
-3.250 0.1842 0.01048 0.00382 -0.0916 0.7624 0.0714
-3.000 0.2041 0.01027 0.00353 -0.0897 0.7412 0.0773
-2.750 0.2242 0.01017 0.00333 -0.0878 0.7208 0.0837
-2.250 0.2610 0.00981 0.00301 -0.0835 0.6839 0.1325
-2.000 0.2777 0.00964 0.00306 -0.0811 0.6665 0.2070
-1.750 0.2982 0.00981 0.00315 -0.0793 0.6496 0.2367
-1.500 0.3190 0.01000 0.00323 -0.0776 0.6344 0.2503
-1.250 0.3392 0.01015 0.00331 -0.0758 0.6197 0.2594
-1.000 0.3595 0.01034 0.00338 -0.0740 0.6046 0.2674
-0.750 0.3791 0.01042 0.00342 -0.0721 0.5905 0.2744
-0.500 0.3988 0.01054 0.00345 -0.0702 0.5767 0.2803
-0.250 0.4173 0.01061 0.00345 -0.0681 0.5621 0.2852
0.000 0.4339 0.01066 0.00344 -0.0656 0.5469 0.2896
0.250 0.4502 0.01075 0.00346 -0.0630 0.5307 0.2951
0.500 0.4669 0.01088 0.00347 -0.0606 0.5144 0.2986
0.750 0.4835 0.01089 0.00343 -0.0581 0.4989 0.3024
1.250 0.5197 0.01109 0.00350 -0.0539 0.4732 0.3112
1.500 0.5388 0.01118 0.00353 -0.0521 0.4637 0.3160
1.750 0.5579 0.01125 0.00357 -0.0503 0.4548 0.3190
2.000 0.5783 0.01133 0.00362 -0.0487 0.4474 0.3216
2.250 0.5984 0.01143 0.00369 -0.0471 0.4397 0.3246
2.500 0.6185 0.01156 0.00377 -0.0455 0.4331 0.3276
2.750 0.6396 0.01164 0.00384 -0.0441 0.4266 0.3302
3.000 0.6584 0.01172 0.00391 -0.0423 0.4204 0.3343
3.250 0.6790 0.01180 0.00399 -0.0409 0.4144 0.3377
3.500 0.6995 0.01189 0.00408 -0.0394 0.4081 0.3405
3.750 0.7189 0.01205 0.00420 -0.0378 0.4021 0.3432
4.000 0.7398 0.01211 0.00429 -0.0364 0.3962 0.3473
4.250 0.7590 0.01221 0.00440 -0.0347 0.3896 0.3514
4.500 0.7778 0.01235 0.00453 -0.0330 0.3833 0.3569
4.750 0.7979 0.01241 0.00465 -0.0315 0.3760 0.3644
5.000 0.8149 0.01254 0.00480 -0.0295 0.3686 0.3802
5.250 0.9712 0.01224 0.00594 -0.0582 0.3474 0.9808
5.500 1.0228 0.01267 0.00630 -0.0637 0.3336 0.9889
5.750 1.0719 0.01309 0.00663 -0.0687 0.3189 0.9952
6.000 1.1275 0.01348 0.00693 -0.0753 0.3035 0.9998
6.250 1.1424 0.01372 0.00714 -0.0729 0.2949 1.0000
6.500 1.1526 0.01403 0.00739 -0.0696 0.2880 1.0000
6.750 1.1657 0.01428 0.00763 -0.0669 0.2813 1.0000
7.000 1.1761 0.01462 0.00793 -0.0638 0.2749 1.0000
7.250 1.1894 0.01490 0.00821 -0.0612 0.2698 1.0000
7.500 1.2025 0.01519 0.00849 -0.0586 0.2653 1.0000
7.750 1.2144 0.01554 0.00883 -0.0558 0.2613 1.0000
8.000 1.2257 0.01595 0.00921 -0.0530 0.2576 1.0000
8.250 1.2411 0.01621 0.00952 -0.0509 0.2545 1.0000
8.500 1.2556 0.01652 0.00985 -0.0487 0.2515 1.0000
8.750 1.2692 0.01689 0.01023 -0.0465 0.2488 1.0000
9.000 1.2817 0.01732 0.01066 -0.0440 0.2460 1.0000
9.250 1.2938 0.01781 0.01114 -0.0416 0.2431 1.0000
9.500 1.3090 0.01814 0.01152 -0.0397 0.2404 1.0000
9.750 1.3239 0.01848 0.01191 -0.0378 0.2365 1.0000
10.000 1.3375 0.01891 0.01236 -0.0358 0.2332 1.0000
10.250 1.3492 0.01945 0.01290 -0.0336 0.2300 1.0000
10.500 1.3613 0.02004 0.01348 -0.0314 0.2267 1.0000
10.750 1.3767 0.02041 0.01394 -0.0298 0.2242 1.0000
11.000 1.3911 0.02086 0.01445 -0.0281 0.2212 1.0000
11.250 1.4044 0.02139 0.01502 -0.0263 0.2184 1.0000
11.500 1.4154 0.02205 0.01569 -0.0243 0.2151 1.0000
11.750 1.4258 0.02280 0.01644 -0.0223 0.2116 1.0000
12.000 1.4406 0.02329 0.01704 -0.0208 0.2091 1.0000
12.250 1.4543 0.02385 0.01768 -0.0194 0.2056 1.0000
12.500 1.4652 0.02459 0.01844 -0.0176 0.2015 1.0000
12.750 1.4726 0.02559 0.01943 -0.0156 0.1974 1.0000
13.000 1.4873 0.02618 0.02013 -0.0145 0.1938 1.0000
13.250 1.4991 0.02695 0.02097 -0.0132 0.1880 1.0000
13.500 1.5061 0.02808 0.02210 -0.0114 0.1835 1.0000
13.750 1.5194 0.02885 0.02296 -0.0104 0.1773 1.0000
14.000 1.5257 0.03014 0.02424 -0.0088 0.1694 1.0000
14.250 1.5324 0.03146 0.02557 -0.0075 0.1571 1.0000
14.500 1.5310 0.03346 0.02751 -0.0057 0.1416 1.0000
14.750 1.5231 0.03612 0.03009 -0.0038 0.1253 1.0000
15.000 1.5132 0.03911 0.03304 -0.0021 0.1123 1.0000
15.250 1.4982 0.04275 0.03663 -0.0006 0.0981 1.0000
15.500 1.4844 0.04647 0.04034 0.0004 0.0852 1.0000
15.750 1.4551 0.05204 0.04581 0.0014 0.0635 1.0000
16.000 1.4292 0.05755 0.05129 0.0017 0.0483 1.0000
16.250 1.3979 0.06402 0.05777 0.0015 0.0338 1.0000
16.500 1.3760 0.06962 0.06343 0.0010 0.0271 1.0000
16.750 1.3576 0.07502 0.06891 0.0003 0.0238 1.0000
17.000 1.3398 0.08049 0.07448 -0.0007 0.0217 1.0000
17.250 1.3247 0.08567 0.07976 -0.0017 0.0207 1.0000
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