GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 500,000 Max Cl/Cd: 83.11 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe711-il-500000-n5.txt Download as CSV file: xf-goe711-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0618 0.09047 0.08801 -0.0974 0.9466 0.0136
-9.250 -0.0591 0.08715 0.08469 -0.0987 0.9405 0.0140
-9.000 -0.0577 0.08347 0.08101 -0.1002 0.9345 0.0143
-8.750 -0.0745 0.07580 0.07334 -0.1044 0.9272 0.0155
-8.500 -0.0683 0.07354 0.07108 -0.1054 0.9198 0.0156
-8.250 -0.0629 0.07122 0.06876 -0.1066 0.9126 0.0158
-8.000 -0.0600 0.06849 0.06603 -0.1086 0.9035 0.0161
-7.750 -0.0527 0.06493 0.06244 -0.1124 0.8947 0.0164
-7.500 -0.0449 0.06054 0.05797 -0.1169 0.8858 0.0168
-7.000 -0.0354 0.04395 0.04093 -0.1295 0.8644 0.0191
-6.750 -0.0154 0.04240 0.03926 -0.1301 0.8521 0.0193
-6.500 0.0046 0.04041 0.03712 -0.1308 0.8377 0.0197
-6.000 0.0356 0.02676 0.02233 -0.1329 0.8119 0.0229
-5.750 0.0595 0.02558 0.02095 -0.1330 0.7972 0.0232
-5.500 0.0844 0.02462 0.01981 -0.1331 0.7824 0.0236
-5.250 0.1095 0.02361 0.01860 -0.1332 0.7674 0.0240
-5.000 0.1348 0.02248 0.01723 -0.1332 0.7518 0.0246
-4.750 0.1604 0.02093 0.01537 -0.1331 0.7370 0.0255
-4.500 0.1861 0.01894 0.01297 -0.1330 0.7228 0.0262
-4.250 0.2124 0.01741 0.01105 -0.1328 0.7077 0.0268
-4.000 0.2393 0.01661 0.00993 -0.1327 0.6918 0.0274
-3.750 0.2657 0.01570 0.00881 -0.1327 0.6764 0.0280
-3.500 0.2926 0.01518 0.00814 -0.1327 0.6616 0.0283
-3.250 0.3194 0.01480 0.00762 -0.1326 0.6457 0.0287
-3.000 0.3462 0.01446 0.00714 -0.1325 0.6290 0.0290
-2.750 0.3729 0.01416 0.00670 -0.1324 0.6124 0.0295
-2.500 0.3996 0.01387 0.00628 -0.1323 0.5968 0.0299
-2.250 0.4263 0.01362 0.00591 -0.1322 0.5818 0.0303
-2.000 0.4529 0.01341 0.00558 -0.1320 0.5661 0.0308
-1.750 0.4793 0.01327 0.00534 -0.1319 0.5499 0.0315
-1.500 0.5056 0.01315 0.00511 -0.1317 0.5343 0.0322
-1.250 0.5320 0.01303 0.00489 -0.1315 0.5197 0.0326
-1.000 0.5585 0.01294 0.00470 -0.1314 0.5061 0.0330
-0.750 0.5850 0.01287 0.00455 -0.1313 0.4925 0.0334
-0.500 0.6112 0.01272 0.00433 -0.1312 0.4789 0.0342
-0.250 0.6374 0.01269 0.00424 -0.1311 0.4658 0.0349
0.000 0.6636 0.01271 0.00419 -0.1309 0.4536 0.0357
0.250 0.6899 0.01274 0.00416 -0.1308 0.4424 0.0367
0.500 0.7163 0.01279 0.00416 -0.1307 0.4320 0.0381
0.750 0.7422 0.01287 0.00417 -0.1305 0.4216 0.0396
1.000 0.7682 0.01294 0.00418 -0.1303 0.4110 0.0408
1.250 0.7942 0.01299 0.00419 -0.1302 0.4018 0.0431
1.500 0.8199 0.01310 0.00425 -0.1299 0.3932 0.0460
1.750 0.8459 0.01319 0.00430 -0.1298 0.3859 0.0497
2.000 0.8714 0.01329 0.00438 -0.1295 0.3784 0.0597
2.250 0.8890 0.01139 0.00475 -0.1280 0.3726 1.0000
2.500 0.9143 0.01158 0.00485 -0.1277 0.3654 1.0000
2.750 0.9389 0.01180 0.00498 -0.1273 0.3589 1.0000
3.000 0.9641 0.01198 0.00511 -0.1270 0.3531 1.0000
3.250 0.9886 0.01220 0.00525 -0.1266 0.3475 1.0000
3.500 1.0128 0.01242 0.00542 -0.1261 0.3428 1.0000
3.750 1.0375 0.01260 0.00557 -0.1258 0.3383 1.0000
4.000 1.0611 0.01284 0.00575 -0.1252 0.3328 1.0000
4.250 1.0838 0.01310 0.00596 -0.1245 0.3269 1.0000
4.500 1.1070 0.01332 0.00615 -0.1238 0.3213 1.0000
4.750 1.1276 0.01359 0.00638 -0.1227 0.3152 1.0000
5.000 1.1487 0.01387 0.00662 -0.1217 0.3095 1.0000
5.250 1.1704 0.01413 0.00686 -0.1208 0.3037 1.0000
5.500 1.1910 0.01445 0.00714 -0.1197 0.2987 1.0000
5.750 1.2126 0.01473 0.00741 -0.1189 0.2952 1.0000
6.000 1.2349 0.01499 0.00768 -0.1181 0.2918 1.0000
6.250 1.2565 0.01528 0.00797 -0.1174 0.2882 1.0000
6.500 1.2775 0.01561 0.00829 -0.1165 0.2846 1.0000
6.750 1.2977 0.01598 0.00865 -0.1155 0.2812 1.0000
7.000 1.3198 0.01627 0.00897 -0.1148 0.2782 1.0000
7.250 1.3412 0.01659 0.00930 -0.1141 0.2745 1.0000
7.500 1.3615 0.01696 0.00969 -0.1132 0.2703 1.0000
7.750 1.3803 0.01742 0.01012 -0.1120 0.2643 1.0000
8.000 1.4000 0.01783 0.01052 -0.1111 0.2560 1.0000
8.250 1.4177 0.01836 0.01101 -0.1099 0.2472 1.0000
8.500 1.4352 0.01891 0.01153 -0.1086 0.2379 1.0000
8.750 1.4529 0.01945 0.01206 -0.1075 0.2301 1.0000
9.000 1.4684 0.02012 0.01268 -0.1060 0.2203 1.0000
9.250 1.4843 0.02077 0.01332 -0.1046 0.2100 1.0000
9.500 1.4976 0.02161 0.01410 -0.1030 0.1965 1.0000
9.750 1.5062 0.02274 0.01512 -0.1007 0.1769 1.0000
10.000 1.4975 0.02504 0.01711 -0.0962 0.1321 1.0000
10.250 1.4980 0.02683 0.01879 -0.0931 0.1114 1.0000
10.500 1.4929 0.02908 0.02090 -0.0896 0.0750 1.0000
10.750 1.4877 0.03145 0.02321 -0.0864 0.0547 1.0000
11.000 1.4960 0.03288 0.02470 -0.0848 0.0500 1.0000
11.250 1.5037 0.03440 0.02628 -0.0832 0.0460 1.0000
11.500 1.5121 0.03589 0.02784 -0.0819 0.0409 1.0000
12.000 1.5154 0.04030 0.03224 -0.0786 0.0169 1.0000
12.250 1.5204 0.04233 0.03437 -0.0774 0.0153 1.0000
12.500 1.5237 0.04460 0.03673 -0.0763 0.0141 1.0000
12.750 1.5264 0.04700 0.03922 -0.0753 0.0132 1.0000
13.000 1.5300 0.04938 0.04169 -0.0745 0.0126 1.0000
13.250 1.5319 0.05201 0.04443 -0.0737 0.0120 1.0000
13.500 1.5323 0.05489 0.04742 -0.0731 0.0116 1.0000
13.750 1.5308 0.05808 0.05070 -0.0726 0.0112 1.0000
14.000 1.5269 0.06163 0.05437 -0.0721 0.0108 1.0000
14.250 1.5199 0.06566 0.05853 -0.0718 0.0104 1.0000
14.500 1.5160 0.06940 0.06238 -0.0717 0.0102 1.0000
14.750 1.5107 0.07340 0.06650 -0.0718 0.0099 1.0000
15.000 1.5040 0.07768 0.07090 -0.0720 0.0097 1.0000
15.250 1.4956 0.08221 0.07555 -0.0723 0.0094 1.0000
15.500 1.4860 0.08702 0.08048 -0.0727 0.0092 1.0000
15.750 1.4752 0.09206 0.08565 -0.0733 0.0090 1.0000
16.000 1.4639 0.09724 0.09095 -0.0741 0.0089 1.0000
16.250 1.4519 0.10257 0.09639 -0.0749 0.0087 1.0000
16.500 1.4394 0.10803 0.10198 -0.0760 0.0086 1.0000
16.750 1.4270 0.11355 0.10761 -0.0772 0.0085 1.0000
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