GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 500,000 Max Cl/Cd: 64.19 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe506-il-500000.txt Download as CSV file: xf-goe506-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3529 0.07272 0.07003 -0.1156 0.9742 0.0198
-13.000 -0.3748 0.06286 0.06002 -0.1255 0.9724 0.0196
-12.750 -0.3966 0.05386 0.05079 -0.1357 0.9685 0.0196
-12.500 -0.4104 0.04723 0.04397 -0.1429 0.9635 0.0193
-12.250 -0.4198 0.04121 0.03762 -0.1510 0.9600 0.0194
-12.000 -0.4228 0.03667 0.03264 -0.1569 0.9567 0.0198
-11.750 -0.4277 0.03488 0.03058 -0.1559 0.9484 0.0200
-11.500 -0.4226 0.03105 0.02650 -0.1567 0.9442 0.0204
-11.250 -0.4150 0.02982 0.02519 -0.1548 0.9380 0.0207
-11.000 -0.3962 0.02928 0.02468 -0.1544 0.9334 0.0212
-10.750 -0.3787 0.02813 0.02341 -0.1541 0.9295 0.0218
-10.500 -0.3715 0.02697 0.02209 -0.1516 0.9236 0.0221
-10.250 -0.3623 0.02583 0.02076 -0.1492 0.9177 0.0227
-10.000 -0.3460 0.02450 0.01921 -0.1481 0.9135 0.0232
-9.750 -0.3358 0.02368 0.01820 -0.1453 0.9079 0.0237
-9.500 -0.3244 0.02324 0.01753 -0.1426 0.9018 0.0242
-9.250 -0.3016 0.02115 0.01535 -0.1426 0.8980 0.0249
-9.000 -0.2840 0.02060 0.01480 -0.1411 0.8929 0.0258
-8.750 -0.2668 0.01995 0.01410 -0.1394 0.8875 0.0265
-8.500 -0.2446 0.01934 0.01341 -0.1386 0.8833 0.0277
-8.250 -0.2199 0.01867 0.01260 -0.1382 0.8798 0.0284
-8.000 -0.2058 0.01832 0.01217 -0.1355 0.8741 0.0290
-7.750 -0.1864 0.01713 0.01093 -0.1343 0.8696 0.0300
-7.500 -0.1639 0.01634 0.01013 -0.1336 0.8658 0.0311
-7.250 -0.1449 0.01589 0.00966 -0.1320 0.8610 0.0322
-7.000 -0.1264 0.01544 0.00916 -0.1303 0.8554 0.0334
-6.750 -0.1032 0.01497 0.00862 -0.1294 0.8512 0.0344
-6.500 -0.0784 0.01461 0.00818 -0.1288 0.8475 0.0351
-6.250 -0.0664 0.01390 0.00745 -0.1258 0.8416 0.0362
-6.000 -0.0468 0.01335 0.00687 -0.1243 0.8368 0.0378
-5.750 -0.0221 0.01293 0.00639 -0.1237 0.8330 0.0394
-5.500 -0.0042 0.01262 0.00605 -0.1217 0.8273 0.0405
-5.250 0.0182 0.01232 0.00569 -0.1205 0.8221 0.0418
-5.000 0.0426 0.01190 0.00519 -0.1198 0.8180 0.0438
-4.750 0.0624 0.01160 0.00487 -0.1182 0.8127 0.0460
-4.500 0.0849 0.01134 0.00458 -0.1170 0.8078 0.0484
-4.250 0.1105 0.01111 0.00428 -0.1165 0.8038 0.0516
-4.000 0.1335 0.01080 0.00401 -0.1155 0.7993 0.0634
-3.750 0.1471 0.01001 0.00375 -0.1130 0.7938 0.1931
-3.500 0.1726 0.00987 0.00366 -0.1124 0.7892 0.2214
-3.250 0.1979 0.00977 0.00357 -0.1118 0.7840 0.2376
-3.000 0.2199 0.00969 0.00348 -0.1105 0.7768 0.2491
-2.750 0.2459 0.00960 0.00334 -0.1100 0.7695 0.2590
-2.500 0.2668 0.00950 0.00326 -0.1085 0.7616 0.2677
-2.250 0.2929 0.00944 0.00314 -0.1081 0.7549 0.2761
-2.000 0.3130 0.00935 0.00307 -0.1064 0.7459 0.2852
-1.750 0.3358 0.00928 0.00298 -0.1053 0.7367 0.2967
-1.500 0.3572 0.00921 0.00291 -0.1038 0.7264 0.3115
-1.250 0.3772 0.00913 0.00287 -0.1021 0.7165 0.3286
-1.000 0.3977 0.00905 0.00282 -0.1006 0.7063 0.3493
-0.500 0.4313 0.00886 0.00276 -0.0958 0.6785 0.4136
-0.250 0.4436 0.00876 0.00273 -0.0925 0.6579 0.4516
0.000 0.4445 0.00873 0.00269 -0.0867 0.6185 0.4901
0.250 0.4254 0.00909 0.00282 -0.0768 0.5491 0.5235
0.500 0.4191 0.00943 0.00311 -0.0699 0.5090 0.5815
0.750 0.4197 0.00954 0.00337 -0.0644 0.4825 0.6665
1.000 0.4212 0.00952 0.00363 -0.0589 0.4591 0.7776
1.250 0.5468 0.01011 0.00432 -0.0806 0.4101 0.9408
1.500 0.5948 0.01062 0.00465 -0.0852 0.3892 0.9706
1.750 0.6313 0.01101 0.00491 -0.0874 0.3761 0.9869
2.000 0.6738 0.01136 0.00516 -0.0909 0.3660 0.9963
2.250 0.7096 0.01168 0.00537 -0.0930 0.3581 1.0000
2.500 0.7212 0.01182 0.00548 -0.0899 0.3537 1.0000
2.750 0.7331 0.01200 0.00561 -0.0870 0.3491 1.0000
3.000 0.7451 0.01223 0.00578 -0.0840 0.3450 1.0000
3.250 0.7592 0.01244 0.00596 -0.0815 0.3416 1.0000
3.500 0.7759 0.01261 0.00611 -0.0795 0.3384 1.0000
3.750 0.7922 0.01281 0.00629 -0.0775 0.3354 1.0000
4.000 0.8084 0.01304 0.00649 -0.0754 0.3321 1.0000
4.250 0.8241 0.01332 0.00671 -0.0734 0.3288 1.0000
4.500 0.8410 0.01359 0.00695 -0.0715 0.3261 1.0000
4.750 0.8605 0.01377 0.00715 -0.0702 0.3239 1.0000
5.000 0.8798 0.01398 0.00737 -0.0688 0.3214 1.0000
5.250 0.8985 0.01422 0.00760 -0.0674 0.3185 1.0000
5.500 0.9171 0.01449 0.00785 -0.0659 0.3160 1.0000
5.750 0.9354 0.01479 0.00813 -0.0645 0.3133 1.0000
6.000 0.9538 0.01513 0.00843 -0.0631 0.3107 1.0000
6.250 0.9743 0.01535 0.00868 -0.0620 0.3087 1.0000
6.500 0.9947 0.01558 0.00895 -0.0610 0.3066 1.0000
6.750 1.0150 0.01584 0.00923 -0.0600 0.3042 1.0000
7.000 1.0347 0.01612 0.00952 -0.0589 0.3016 1.0000
7.250 1.0538 0.01644 0.00985 -0.0578 0.2990 1.0000
7.500 1.0726 0.01680 0.01020 -0.0566 0.2964 1.0000
7.750 1.0921 0.01714 0.01054 -0.0556 0.2938 1.0000
8.000 1.1127 0.01739 0.01086 -0.0547 0.2904 1.0000
8.250 1.1316 0.01772 0.01121 -0.0536 0.2852 1.0000
8.500 1.1477 0.01819 0.01164 -0.0522 0.2791 1.0000
8.750 1.1686 0.01846 0.01197 -0.0515 0.2742 1.0000
9.000 1.1866 0.01886 0.01239 -0.0504 0.2671 1.0000
9.250 1.2048 0.01928 0.01281 -0.0493 0.2594 1.0000
9.500 1.2211 0.01980 0.01330 -0.0481 0.2486 1.0000
9.750 1.2390 0.02026 0.01377 -0.0471 0.2375 1.0000
10.000 1.2505 0.02108 0.01445 -0.0453 0.2105 1.0000
10.250 1.2566 0.02225 0.01543 -0.0430 0.1862 1.0000
10.500 1.2659 0.02327 0.01639 -0.0411 0.1759 1.0000
10.750 1.2761 0.02426 0.01734 -0.0394 0.1697 1.0000
11.000 1.2891 0.02509 0.01821 -0.0380 0.1652 1.0000
11.250 1.3013 0.02599 0.01913 -0.0366 0.1609 1.0000
11.500 1.3096 0.02716 0.02028 -0.0349 0.1554 1.0000
11.750 1.3233 0.02800 0.02118 -0.0337 0.1503 1.0000
12.000 1.3343 0.02905 0.02224 -0.0324 0.1437 1.0000
12.250 1.3461 0.03006 0.02325 -0.0312 0.1332 1.0000
12.500 1.3448 0.03204 0.02496 -0.0290 0.0892 1.0000
12.750 1.3217 0.03581 0.02851 -0.0252 0.0500 1.0000
13.000 1.3081 0.03905 0.03166 -0.0227 0.0271 1.0000
13.250 1.3067 0.04142 0.03409 -0.0211 0.0231 1.0000
13.500 1.3074 0.04369 0.03645 -0.0198 0.0212 1.0000
13.750 1.3101 0.04585 0.03871 -0.0188 0.0203 1.0000
14.000 1.3107 0.04826 0.04122 -0.0179 0.0196 1.0000
14.250 1.3075 0.05116 0.04423 -0.0170 0.0187 1.0000
14.500 1.3010 0.05455 0.04773 -0.0163 0.0180 1.0000
14.750 1.2929 0.05829 0.05159 -0.0158 0.0177 1.0000
15.000 1.2905 0.06150 0.05491 -0.0157 0.0172 1.0000
15.250 1.2841 0.06534 0.05887 -0.0158 0.0169 1.0000
15.500 1.2779 0.06929 0.06293 -0.0161 0.0166 1.0000
15.750 1.2674 0.07392 0.06769 -0.0167 0.0162 1.0000
16.000 1.2570 0.07860 0.07249 -0.0174 0.0162 1.0000
16.250 1.2453 0.08354 0.07756 -0.0183 0.0159 1.0000
16.500 1.2338 0.08851 0.08264 -0.0193 0.0157 1.0000
16.750 1.2200 0.09386 0.08811 -0.0204 0.0156 1.0000
17.000 1.2074 0.09909 0.09344 -0.0216 0.0154 1.0000
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