GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 500,000 Max Cl/Cd: 61.92 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe506-il-500000-n5.txt Download as CSV file: xf-goe506-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 506 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4759 0.09442 0.09165 -0.0939 0.9782 0.0106
-15.750 -0.5312 0.07991 0.07687 -0.1031 0.9753 0.0104
-15.500 -0.5535 0.07213 0.06894 -0.1086 0.9712 0.0104
-15.250 -0.5740 0.06474 0.06138 -0.1141 0.9668 0.0105
-15.000 -0.5806 0.05894 0.05544 -0.1195 0.9636 0.0107
-14.750 -0.5893 0.05295 0.04929 -0.1251 0.9597 0.0108
-14.500 -0.5959 0.04707 0.04324 -0.1309 0.9547 0.0108
-14.250 -0.5926 0.04189 0.03789 -0.1374 0.9509 0.0109
-14.000 -0.5798 0.03750 0.03330 -0.1441 0.9480 0.0112
-13.750 -0.5692 0.03327 0.02885 -0.1505 0.9428 0.0114
-13.500 -0.5527 0.03012 0.02554 -0.1560 0.9379 0.0117
-13.250 -0.5318 0.02780 0.02309 -0.1606 0.9334 0.0120
-13.000 -0.5175 0.02625 0.02143 -0.1621 0.9267 0.0123
-12.750 -0.4986 0.02510 0.02017 -0.1636 0.9211 0.0126
-12.500 -0.4853 0.02392 0.01887 -0.1637 0.9153 0.0129
-12.250 -0.4773 0.02297 0.01782 -0.1622 0.9088 0.0131
-12.000 -0.4652 0.02212 0.01684 -0.1611 0.9037 0.0135
-11.750 -0.4575 0.02136 0.01597 -0.1588 0.8984 0.0139
-11.500 -0.4517 0.02066 0.01516 -0.1558 0.8928 0.0142
-11.250 -0.4421 0.01999 0.01435 -0.1533 0.8880 0.0146
-11.000 -0.4344 0.01944 0.01375 -0.1503 0.8835 0.0149
-10.750 -0.4252 0.01907 0.01334 -0.1473 0.8785 0.0153
-10.500 -0.4093 0.01868 0.01290 -0.1455 0.8744 0.0156
-10.250 -0.3898 0.01833 0.01248 -0.1444 0.8709 0.0162
-10.000 -0.3740 0.01800 0.01209 -0.1424 0.8666 0.0168
-9.750 -0.3586 0.01759 0.01160 -0.1404 0.8615 0.0174
-9.500 -0.3402 0.01715 0.01104 -0.1389 0.8564 0.0181
-9.250 -0.3238 0.01669 0.01052 -0.1371 0.8519 0.0186
-9.000 -0.3068 0.01632 0.01013 -0.1352 0.8463 0.0191
-8.750 -0.2862 0.01600 0.00975 -0.1341 0.8420 0.0197
-8.500 -0.2644 0.01571 0.00939 -0.1331 0.8385 0.0206
-8.250 -0.2455 0.01541 0.00905 -0.1315 0.8335 0.0215
-8.000 -0.2245 0.01512 0.00868 -0.1303 0.8283 0.0223
-7.750 -0.2039 0.01471 0.00818 -0.1291 0.8238 0.0230
-7.500 -0.1861 0.01432 0.00777 -0.1273 0.8181 0.0237
-7.250 -0.1653 0.01399 0.00740 -0.1260 0.8127 0.0245
-7.000 -0.1430 0.01371 0.00707 -0.1250 0.8078 0.0256
-6.750 -0.1224 0.01345 0.00676 -0.1236 0.8012 0.0265
-6.500 -0.1000 0.01319 0.00641 -0.1225 0.7944 0.0274
-6.250 -0.0784 0.01297 0.00614 -0.1213 0.7877 0.0280
-6.000 -0.0588 0.01254 0.00564 -0.1198 0.7814 0.0293
-5.750 -0.0368 0.01226 0.00532 -0.1187 0.7760 0.0304
-5.500 -0.0147 0.01202 0.00503 -0.1175 0.7697 0.0314
-5.250 0.0084 0.01181 0.00474 -0.1166 0.7637 0.0326
-5.000 0.0311 0.01163 0.00451 -0.1155 0.7574 0.0336
-4.750 0.0540 0.01147 0.00427 -0.1145 0.7496 0.0344
-4.500 0.0764 0.01127 0.00402 -0.1134 0.7430 0.0357
-4.250 0.0993 0.01108 0.00379 -0.1124 0.7369 0.0376
-4.000 0.1224 0.01094 0.00359 -0.1114 0.7304 0.0397
-3.750 0.1454 0.01082 0.00343 -0.1104 0.7236 0.0419
-3.500 0.1679 0.01070 0.00327 -0.1092 0.7158 0.0472
-3.250 0.1840 0.01019 0.00299 -0.1070 0.7048 0.1131
-3.000 0.2025 0.00989 0.00291 -0.1052 0.6950 0.1856
-2.750 0.2227 0.00986 0.00285 -0.1036 0.6815 0.2009
-2.500 0.2418 0.00983 0.00280 -0.1017 0.6647 0.2124
-2.250 0.2567 0.00986 0.00274 -0.0989 0.6371 0.2218
-2.000 0.2412 0.01028 0.00276 -0.0897 0.5488 0.2250
-1.750 0.2405 0.01062 0.00287 -0.0838 0.5076 0.2282
-1.250 0.2652 0.01098 0.00302 -0.0776 0.4636 0.2392
-1.000 0.2804 0.01115 0.00310 -0.0751 0.4445 0.2459
-0.750 0.2957 0.01133 0.00320 -0.0726 0.4235 0.2537
-0.500 0.3114 0.01149 0.00330 -0.0703 0.4046 0.2647
-0.250 0.3267 0.01166 0.00342 -0.0679 0.3859 0.2756
0.000 0.3430 0.01183 0.00353 -0.0657 0.3705 0.2886
0.250 0.3605 0.01197 0.00364 -0.0638 0.3600 0.3024
0.750 0.3958 0.01218 0.00390 -0.0601 0.3418 0.3500
1.000 0.4133 0.01232 0.00404 -0.0582 0.3340 0.3708
1.250 0.4324 0.01240 0.00417 -0.0567 0.3293 0.3946
1.500 0.4518 0.01248 0.00429 -0.0552 0.3249 0.4194
1.750 0.4702 0.01256 0.00444 -0.0535 0.3206 0.4510
2.000 0.4880 0.01261 0.00460 -0.0517 0.3172 0.4914
2.250 0.5047 0.01261 0.00478 -0.0497 0.3144 0.5547
2.500 0.5208 0.01254 0.00495 -0.0476 0.3117 0.6314
3.000 0.7028 0.01249 0.00572 -0.0756 0.3011 0.9705
3.250 0.7356 0.01280 0.00599 -0.0771 0.2979 0.9915
3.750 0.7816 0.01329 0.00643 -0.0758 0.2933 1.0000
4.000 0.7996 0.01348 0.00661 -0.0742 0.2909 1.0000
4.250 0.8178 0.01370 0.00681 -0.0726 0.2888 1.0000
4.500 0.8358 0.01394 0.00703 -0.0709 0.2864 1.0000
4.750 0.8537 0.01420 0.00726 -0.0694 0.2839 1.0000
5.000 0.8721 0.01446 0.00751 -0.0679 0.2816 1.0000
5.250 0.8921 0.01467 0.00774 -0.0667 0.2797 1.0000
5.500 0.9120 0.01490 0.00797 -0.0656 0.2775 1.0000
5.750 0.9317 0.01515 0.00822 -0.0644 0.2745 1.0000
6.000 0.9509 0.01544 0.00850 -0.0632 0.2714 1.0000
6.250 0.9699 0.01574 0.00880 -0.0620 0.2689 1.0000
6.500 0.9890 0.01605 0.00910 -0.0608 0.2662 1.0000
6.750 1.0095 0.01631 0.00939 -0.0598 0.2630 1.0000
7.000 1.0291 0.01662 0.00970 -0.0588 0.2587 1.0000
7.250 1.0476 0.01698 0.01005 -0.0576 0.2536 1.0000
7.500 1.0671 0.01732 0.01039 -0.0566 0.2474 1.0000
7.750 1.0848 0.01775 0.01078 -0.0554 0.2372 1.0000
8.000 1.1001 0.01830 0.01125 -0.0539 0.2165 1.0000
8.250 1.1074 0.01933 0.01203 -0.0514 0.1807 1.0000
8.500 1.1206 0.02006 0.01270 -0.0497 0.1713 1.0000
8.750 1.1340 0.02080 0.01340 -0.0480 0.1641 1.0000
9.000 1.1500 0.02139 0.01399 -0.0468 0.1604 1.0000
9.250 1.1661 0.02198 0.01460 -0.0456 0.1573 1.0000
9.500 1.1820 0.02260 0.01524 -0.0444 0.1547 1.0000
9.750 1.1968 0.02330 0.01595 -0.0431 0.1516 1.0000
10.000 1.2104 0.02408 0.01674 -0.0417 0.1481 1.0000
10.250 1.2259 0.02475 0.01744 -0.0406 0.1454 1.0000
10.500 1.2431 0.02532 0.01806 -0.0397 0.1434 1.0000
10.750 1.2588 0.02600 0.01878 -0.0387 0.1401 1.0000
11.000 1.2733 0.02677 0.01958 -0.0376 0.1367 1.0000
11.250 1.2850 0.02774 0.02055 -0.0363 0.1319 1.0000
11.500 1.3005 0.02847 0.02130 -0.0354 0.1242 1.0000
11.750 1.2987 0.03042 0.02298 -0.0329 0.0833 1.0000
12.000 1.2960 0.03253 0.02503 -0.0305 0.0659 1.0000
12.250 1.2775 0.03597 0.02831 -0.0271 0.0246 1.0000
12.500 1.2807 0.03783 0.03021 -0.0256 0.0191 1.0000
12.750 1.2847 0.03968 0.03211 -0.0243 0.0163 1.0000
13.000 1.2910 0.04139 0.03390 -0.0233 0.0150 1.0000
13.250 1.2972 0.04315 0.03573 -0.0223 0.0143 1.0000
13.500 1.3001 0.04524 0.03789 -0.0213 0.0132 1.0000
13.750 1.3024 0.04748 0.04021 -0.0204 0.0126 1.0000
14.000 1.3041 0.04985 0.04268 -0.0196 0.0121 1.0000
14.250 1.3068 0.05219 0.04510 -0.0190 0.0114 1.0000
14.500 1.3076 0.05480 0.04781 -0.0185 0.0111 1.0000
14.750 1.3067 0.05767 0.05078 -0.0182 0.0107 1.0000
15.000 1.3046 0.06079 0.05400 -0.0180 0.0104 1.0000
15.250 1.3006 0.06428 0.05759 -0.0180 0.0100 1.0000
15.500 1.2938 0.06823 0.06165 -0.0182 0.0098 1.0000
15.750 1.2853 0.07252 0.06605 -0.0186 0.0096 1.0000
16.000 1.2755 0.07706 0.07072 -0.0192 0.0095 1.0000
16.250 1.2650 0.08178 0.07556 -0.0200 0.0093 1.0000
16.500 1.2559 0.08637 0.08027 -0.0208 0.0092 1.0000
16.750 1.2471 0.09093 0.08494 -0.0217 0.0090 1.0000
17.000 1.2360 0.09587 0.09000 -0.0228 0.0090 1.0000
17.250 1.2277 0.10046 0.09469 -0.0239 0.0086 1.0000
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Polar data table (+)
Polar graphs
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