GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 500,000 Max Cl/Cd: 96.62 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe535-il-500000.txt Download as CSV file: xf-goe535-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2445 0.13351 0.13097 -0.0366 1.0000 0.0458
-12.500 -0.7288 0.04432 0.04085 -0.0918 0.9955 0.0416
-12.250 -0.7259 0.03709 0.03333 -0.1054 0.9861 0.0419
-12.000 -0.6948 0.03201 0.02798 -0.1177 0.9812 0.0425
-11.750 -0.6679 0.02903 0.02474 -0.1236 0.9759 0.0430
-11.500 -0.6392 0.02681 0.02228 -0.1275 0.9709 0.0436
-11.250 -0.6044 0.02509 0.02031 -0.1314 0.9680 0.0441
-11.000 -0.5669 0.02350 0.01870 -0.1348 0.9660 0.0450
-10.750 -0.5379 0.02277 0.01797 -0.1356 0.9590 0.0455
-10.500 -0.5009 0.02192 0.01708 -0.1380 0.9553 0.0463
-10.250 -0.4628 0.02089 0.01596 -0.1408 0.9528 0.0471
-10.000 -0.4249 0.01986 0.01479 -0.1434 0.9503 0.0481
-9.750 -0.4006 0.01907 0.01384 -0.1432 0.9409 0.0489
-9.500 -0.3671 0.01804 0.01279 -0.1448 0.9356 0.0498
-9.250 -0.3380 0.01755 0.01230 -0.1451 0.9269 0.0506
-9.000 -0.3054 0.01704 0.01175 -0.1460 0.9183 0.0516
-8.750 -0.2774 0.01653 0.01115 -0.1460 0.9066 0.0527
-8.500 -0.2464 0.01601 0.01047 -0.1466 0.8956 0.0540
-8.250 -0.2197 0.01543 0.00985 -0.1464 0.8812 0.0552
-8.000 -0.1920 0.01519 0.00958 -0.1461 0.8655 0.0564
-7.750 -0.1645 0.01493 0.00923 -0.1458 0.8484 0.0579
-7.500 -0.1376 0.01464 0.00878 -0.1454 0.8303 0.0595
-7.250 -0.1121 0.01422 0.00825 -0.1448 0.8126 0.0609
-7.000 -0.0860 0.01404 0.00801 -0.1442 0.7951 0.0623
-6.500 -0.0339 0.01375 0.00745 -0.1429 0.7613 0.0659
-6.250 -0.0089 0.01341 0.00706 -0.1422 0.7457 0.0677
-6.000 0.0171 0.01330 0.00689 -0.1416 0.7315 0.0695
-5.750 0.0434 0.01320 0.00668 -0.1410 0.7179 0.0716
-5.500 0.0696 0.01301 0.00639 -0.1404 0.7054 0.0735
-5.250 0.0948 0.01274 0.00608 -0.1397 0.6930 0.0755
-5.000 0.1212 0.01259 0.00590 -0.1391 0.6805 0.0775
-4.750 0.1476 0.01251 0.00571 -0.1385 0.6686 0.0797
-4.500 0.1734 0.01225 0.00539 -0.1379 0.6567 0.0818
-4.250 0.1994 0.01206 0.00519 -0.1373 0.6458 0.0840
-4.000 0.2256 0.01195 0.00502 -0.1366 0.6340 0.0863
-3.750 0.2523 0.01187 0.00487 -0.1361 0.6225 0.0884
-3.500 0.2775 0.01164 0.00458 -0.1353 0.6106 0.0909
-3.250 0.3039 0.01149 0.00442 -0.1348 0.5991 0.0934
-3.000 0.3300 0.01143 0.00428 -0.1341 0.5878 0.0960
-2.750 0.3568 0.01137 0.00416 -0.1336 0.5760 0.0982
-2.500 0.3822 0.01117 0.00393 -0.1329 0.5646 0.1013
-2.250 0.4083 0.01109 0.00381 -0.1323 0.5526 0.1043
-2.000 0.4347 0.01106 0.00371 -0.1317 0.5417 0.1075
-1.750 0.4606 0.01098 0.00358 -0.1310 0.5309 0.1112
-1.500 0.4870 0.01091 0.00349 -0.1305 0.5208 0.1162
-1.250 0.5131 0.01088 0.00341 -0.1298 0.5108 0.1227
-1.000 0.5395 0.01080 0.00334 -0.1293 0.5020 0.1347
-0.750 0.5650 0.01055 0.00327 -0.1287 0.4936 0.1937
-0.500 0.5893 0.01020 0.00332 -0.1281 0.4860 0.3378
-0.250 0.6162 0.01025 0.00343 -0.1276 0.4785 0.3757
0.000 0.6424 0.01039 0.00351 -0.1270 0.4712 0.3942
0.250 0.6691 0.01053 0.00361 -0.1264 0.4650 0.4083
0.500 0.6960 0.01060 0.00371 -0.1259 0.4589 0.4197
0.750 0.7223 0.01076 0.00380 -0.1253 0.4526 0.4297
1.000 0.7483 0.01091 0.00393 -0.1247 0.4468 0.4389
1.250 0.7753 0.01100 0.00403 -0.1242 0.4418 0.4482
1.500 0.8017 0.01113 0.00412 -0.1236 0.4362 0.4560
1.750 0.8272 0.01130 0.00426 -0.1229 0.4306 0.4642
2.000 0.8536 0.01144 0.00439 -0.1223 0.4255 0.4721
2.250 0.8798 0.01151 0.00448 -0.1217 0.4199 0.4793
2.500 0.9051 0.01165 0.00461 -0.1210 0.4141 0.4863
2.750 0.9303 0.01190 0.00478 -0.1203 0.4086 0.4941
3.000 0.9565 0.01195 0.00488 -0.1197 0.4047 0.5010
3.250 0.9823 0.01205 0.00501 -0.1191 0.4002 0.5073
3.500 1.0074 0.01221 0.00514 -0.1184 0.3954 0.5136
3.750 1.0320 0.01243 0.00529 -0.1176 0.3902 0.5184
4.000 1.0575 0.01249 0.00541 -0.1169 0.3865 0.5234
4.250 1.0828 0.01258 0.00555 -0.1163 0.3822 0.5289
4.500 1.1074 0.01273 0.00568 -0.1155 0.3778 0.5350
4.750 1.1310 0.01292 0.00583 -0.1145 0.3731 0.5409
5.000 1.1552 0.01306 0.00601 -0.1137 0.3688 0.5469
5.250 1.1796 0.01316 0.00615 -0.1129 0.3642 0.5536
5.500 1.2029 0.01330 0.00630 -0.1119 0.3595 0.5602
5.750 1.2250 0.01349 0.00648 -0.1107 0.3548 0.5671
6.000 1.2479 0.01368 0.00668 -0.1097 0.3504 0.5748
6.250 1.2707 0.01377 0.00685 -0.1086 0.3460 0.5823
6.500 1.2913 0.01391 0.00701 -0.1072 0.3411 0.5907
6.750 1.3100 0.01413 0.00722 -0.1054 0.3363 0.5995
7.000 1.3303 0.01429 0.00744 -0.1039 0.3318 0.6096
7.250 1.3506 0.01443 0.00764 -0.1024 0.3267 0.6202
7.500 1.3686 0.01464 0.00787 -0.1006 0.3210 0.6324
7.750 1.3860 0.01489 0.00816 -0.0987 0.3155 0.6477
8.250 1.4561 0.01507 0.00891 -0.1025 0.3007 1.0000
8.500 1.4766 0.01534 0.00920 -0.1012 0.2950 1.0000
8.750 1.4952 0.01568 0.00953 -0.0997 0.2889 1.0000
9.000 1.5104 0.01617 0.00995 -0.0978 0.2828 1.0000
9.250 1.5303 0.01648 0.01030 -0.0966 0.2765 1.0000
9.500 1.5460 0.01696 0.01075 -0.0948 0.2699 1.0000
9.750 1.5621 0.01746 0.01124 -0.0931 0.2640 1.0000
10.000 1.5789 0.01793 0.01173 -0.0916 0.2577 1.0000
10.250 1.5918 0.01860 0.01235 -0.0896 0.2516 1.0000
10.500 1.6082 0.01913 0.01291 -0.0882 0.2461 1.0000
10.750 1.6227 0.01977 0.01356 -0.0865 0.2404 1.0000
11.000 1.6330 0.02066 0.01441 -0.0845 0.2349 1.0000
11.250 1.6492 0.02126 0.01507 -0.0833 0.2302 1.0000
11.500 1.6616 0.02209 0.01590 -0.0817 0.2247 1.0000
11.750 1.6698 0.02321 0.01698 -0.0798 0.2196 1.0000
12.000 1.6848 0.02395 0.01780 -0.0786 0.2153 1.0000
12.250 1.6961 0.02496 0.01883 -0.0772 0.2108 1.0000
12.500 1.7039 0.02624 0.02010 -0.0756 0.2065 1.0000
12.750 1.7141 0.02740 0.02131 -0.0743 0.2030 1.0000
13.000 1.7258 0.02850 0.02247 -0.0732 0.1995 1.0000
13.250 1.7344 0.02986 0.02387 -0.0720 0.1958 1.0000
13.500 1.7395 0.03154 0.02555 -0.0707 0.1922 1.0000
13.750 1.7464 0.03313 0.02719 -0.0697 0.1891 1.0000
14.000 1.7561 0.03454 0.02868 -0.0688 0.1856 1.0000
14.250 1.7623 0.03628 0.03047 -0.0680 0.1822 1.0000
14.500 1.7642 0.03845 0.03265 -0.0670 0.1787 1.0000
14.750 1.7668 0.04061 0.03486 -0.0662 0.1755 1.0000
15.000 1.7740 0.04241 0.03675 -0.0657 0.1724 1.0000
15.250 1.7773 0.04461 0.03902 -0.0651 0.1689 1.0000
15.500 1.7759 0.04732 0.04175 -0.0645 0.1655 1.0000
15.750 1.7748 0.05006 0.04454 -0.0641 0.1622 1.0000
16.000 1.7779 0.05243 0.04701 -0.0638 0.1586 1.0000
16.250 1.7754 0.05545 0.05008 -0.0636 0.1546 1.0000
16.500 1.7667 0.05919 0.05385 -0.0634 0.1507 1.0000
16.750 1.7678 0.06191 0.05668 -0.0634 0.1462 1.0000
17.000 1.7599 0.06575 0.06056 -0.0635 0.1412 1.0000
17.250 1.7504 0.06982 0.06468 -0.0637 0.1361 1.0000
17.500 1.7392 0.07420 0.06912 -0.0641 0.1296 1.0000
17.750 1.7257 0.07893 0.07390 -0.0647 0.1230 1.0000
18.000 1.7056 0.08461 0.07960 -0.0656 0.1157 1.0000
18.250 1.6872 0.09013 0.08515 -0.0666 0.1081 1.0000
18.500 1.6667 0.09605 0.09110 -0.0678 0.1013 1.0000
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Polar data table (+)
Polar graphs
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