GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 615 AIRFOIL (goe615-il) Reynolds number: 200,000 Max Cl/Cd: 72.15 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe615-il-200000-n5.txt Download as CSV file: xf-goe615-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 615 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1511 0.09049 0.08675 -0.0738 0.9495 0.0365
-9.500 -0.1514 0.08229 0.07852 -0.0829 0.9420 0.0374
-9.250 -0.1390 0.07739 0.07360 -0.0881 0.9335 0.0373
-9.000 -0.1261 0.07190 0.06807 -0.0946 0.9256 0.0373
-8.750 -0.1204 0.06506 0.06118 -0.1027 0.9137 0.0373
-8.500 -0.1075 0.06147 0.05758 -0.1074 0.9020 0.0379
-8.000 -0.1533 0.03919 0.03452 -0.1258 0.8670 0.0381
-7.750 -0.1430 0.03614 0.03119 -0.1265 0.8580 0.0384
-7.500 -0.1343 0.03353 0.02830 -0.1258 0.8476 0.0387
-7.250 -0.1208 0.03097 0.02539 -0.1254 0.8394 0.0391
-7.000 -0.1057 0.02915 0.02331 -0.1245 0.8300 0.0397
-6.750 -0.0873 0.02731 0.02113 -0.1238 0.8223 0.0406
-6.500 -0.0705 0.02557 0.01903 -0.1226 0.8129 0.0414
-6.250 -0.0497 0.02396 0.01703 -0.1218 0.8051 0.0419
-6.000 -0.0296 0.02267 0.01541 -0.1206 0.7957 0.0424
-5.750 -0.0061 0.02155 0.01394 -0.1199 0.7880 0.0429
-5.500 0.0163 0.02059 0.01281 -0.1190 0.7789 0.0434
-5.000 0.0653 0.01927 0.01132 -0.1178 0.7618 0.0449
-4.750 0.0911 0.01870 0.01061 -0.1173 0.7538 0.0459
-4.500 0.1152 0.01814 0.00994 -0.1165 0.7442 0.0468
-4.250 0.1410 0.01756 0.00920 -0.1159 0.7356 0.0476
-4.000 0.1657 0.01705 0.00857 -0.1151 0.7254 0.0484
-3.750 0.1913 0.01661 0.00799 -0.1144 0.7160 0.0492
-3.500 0.2161 0.01611 0.00744 -0.1137 0.7059 0.0501
-3.250 0.2409 0.01569 0.00701 -0.1130 0.6966 0.0513
-3.000 0.2661 0.01538 0.00666 -0.1123 0.6871 0.0529
-2.750 0.2911 0.01509 0.00633 -0.1116 0.6777 0.0546
-2.500 0.3165 0.01483 0.00598 -0.1110 0.6688 0.0561
-2.250 0.3413 0.01460 0.00570 -0.1102 0.6591 0.0574
-2.000 0.3656 0.01431 0.00537 -0.1094 0.6491 0.0592
-1.750 0.3900 0.01413 0.00515 -0.1086 0.6379 0.0617
-1.500 0.4149 0.01400 0.00495 -0.1078 0.6276 0.0648
-1.250 0.4396 0.01386 0.00474 -0.1070 0.6180 0.0686
-1.000 0.4645 0.01375 0.00461 -0.1063 0.6085 0.0730
-0.750 0.4895 0.01366 0.00447 -0.1056 0.5998 0.0801
-0.500 0.5139 0.01353 0.00438 -0.1048 0.5905 0.0980
-0.250 0.5373 0.01324 0.00434 -0.1040 0.5827 0.1788
0.000 0.5613 0.01307 0.00438 -0.1032 0.5752 0.2530
0.250 0.5852 0.01295 0.00441 -0.1024 0.5685 0.3184
0.500 0.6081 0.01273 0.00448 -0.1015 0.5623 0.4150
0.750 0.6277 0.01233 0.00459 -0.0998 0.5561 0.5759
1.250 0.7404 0.01191 0.00483 -0.1112 0.5409 1.0000
1.500 0.7634 0.01207 0.00489 -0.1101 0.5345 1.0000
1.750 0.7865 0.01224 0.00496 -0.1091 0.5284 1.0000
2.000 0.8095 0.01238 0.00505 -0.1080 0.5218 1.0000
2.250 0.8323 0.01257 0.00514 -0.1069 0.5151 1.0000
2.500 0.8551 0.01272 0.00525 -0.1059 0.5083 1.0000
2.750 0.8776 0.01289 0.00537 -0.1047 0.5011 1.0000
3.000 0.9001 0.01308 0.00548 -0.1036 0.4941 1.0000
3.250 0.9222 0.01323 0.00563 -0.1024 0.4858 1.0000
3.500 0.9440 0.01343 0.00574 -0.1012 0.4780 1.0000
3.750 0.9651 0.01358 0.00590 -0.0999 0.4677 1.0000
4.000 0.9854 0.01377 0.00604 -0.0984 0.4563 1.0000
4.250 1.0046 0.01397 0.00618 -0.0967 0.4426 1.0000
4.500 1.0231 0.01418 0.00634 -0.0949 0.4266 1.0000
4.750 1.0404 0.01443 0.00651 -0.0929 0.4072 1.0000
5.000 1.0555 0.01475 0.00671 -0.0905 0.3859 1.0000
5.250 1.0688 0.01513 0.00696 -0.0879 0.3667 1.0000
5.500 1.0815 0.01554 0.00725 -0.0851 0.3512 1.0000
5.750 1.0945 0.01594 0.00758 -0.0825 0.3389 1.0000
6.000 1.1077 0.01637 0.00794 -0.0800 0.3291 1.0000
6.250 1.1221 0.01681 0.00832 -0.0777 0.3195 1.0000
6.500 1.1365 0.01726 0.00873 -0.0755 0.3111 1.0000
6.750 1.1512 0.01773 0.00917 -0.0734 0.3028 1.0000
7.000 1.1653 0.01823 0.00963 -0.0713 0.2943 1.0000
7.250 1.1796 0.01874 0.01011 -0.0693 0.2855 1.0000
7.500 1.1940 0.01927 0.01063 -0.0674 0.2782 1.0000
7.750 1.2096 0.01977 0.01114 -0.0657 0.2713 1.0000
8.250 1.2384 0.02091 0.01227 -0.0622 0.2579 1.0000
8.500 1.2520 0.02154 0.01291 -0.0604 0.2514 1.0000
8.750 1.2657 0.02218 0.01356 -0.0587 0.2456 1.0000
9.000 1.2805 0.02280 0.01421 -0.0572 0.2398 1.0000
9.250 1.2932 0.02354 0.01497 -0.0556 0.2344 1.0000
9.500 1.3067 0.02426 0.01572 -0.0541 0.2295 1.0000
9.750 1.3205 0.02499 0.01650 -0.0527 0.2239 1.0000
10.000 1.3322 0.02585 0.01738 -0.0511 0.2188 1.0000
10.250 1.3441 0.02673 0.01829 -0.0496 0.2129 1.0000
10.500 1.3559 0.02764 0.01926 -0.0482 0.2069 1.0000
10.750 1.3652 0.02874 0.02037 -0.0467 0.2016 1.0000
11.000 1.3774 0.02969 0.02138 -0.0455 0.1961 1.0000
11.250 1.3866 0.03086 0.02259 -0.0441 0.1897 1.0000
11.500 1.3955 0.03208 0.02386 -0.0429 0.1843 1.0000
11.750 1.4058 0.03325 0.02510 -0.0417 0.1789 1.0000
12.000 1.4113 0.03481 0.02667 -0.0404 0.1721 1.0000
12.250 1.4194 0.03621 0.02813 -0.0393 0.1643 1.0000
12.500 1.4230 0.03803 0.02996 -0.0382 0.1553 1.0000
12.750 1.4240 0.04014 0.03207 -0.0370 0.1430 1.0000
13.000 1.4242 0.04241 0.03433 -0.0360 0.1308 1.0000
13.250 1.4199 0.04521 0.03707 -0.0350 0.1138 1.0000
13.500 1.4106 0.04863 0.04040 -0.0342 0.0954 1.0000
13.750 1.4046 0.05185 0.04359 -0.0336 0.0846 1.0000
14.000 1.3986 0.05520 0.04694 -0.0332 0.0775 1.0000
14.250 1.3939 0.05853 0.05030 -0.0330 0.0733 1.0000
14.500 1.3924 0.06158 0.05343 -0.0329 0.0713 1.0000
14.750 1.3883 0.06500 0.05692 -0.0330 0.0691 1.0000
15.000 1.3836 0.06859 0.06059 -0.0333 0.0673 1.0000
15.250 1.3803 0.07211 0.06420 -0.0336 0.0660 1.0000
15.500 1.3781 0.07551 0.06771 -0.0340 0.0651 1.0000
15.750 1.3747 0.07914 0.07146 -0.0345 0.0640 1.0000
16.000 1.3703 0.08296 0.07539 -0.0352 0.0631 1.0000
16.250 1.3655 0.08693 0.07948 -0.0360 0.0624 1.0000
16.500 1.3583 0.09130 0.08396 -0.0370 0.0612 1.0000
16.750 1.3520 0.09561 0.08838 -0.0381 0.0606 1.0000
17.000 1.3432 0.10038 0.09326 -0.0394 0.0596 1.0000
17.250 1.3350 0.10516 0.09813 -0.0409 0.0588 1.0000
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