GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 528 AIRFOIL (goe528-il) Reynolds number: 200,000 Max Cl/Cd: 77.6 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe528-il-200000-n5.txt Download as CSV file: xf-goe528-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 528 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2420 0.14159 0.13780 -0.0421 1.0000 0.0270
-12.750 -0.2398 0.13872 0.13496 -0.0430 1.0000 0.0270
-12.500 -0.2377 0.13585 0.13212 -0.0438 1.0000 0.0271
-12.250 -0.2314 0.13281 0.12912 -0.0434 1.0000 0.0274
-12.000 -0.2246 0.13050 0.12684 -0.0429 1.0000 0.0280
-11.750 -0.2209 0.12815 0.12453 -0.0428 1.0000 0.0284
-11.500 -0.2184 0.12593 0.12237 -0.0425 1.0000 0.0294
-11.250 -0.2039 0.12180 0.11824 -0.0463 0.9948 0.0305
-10.750 -0.1862 0.11349 0.10992 -0.0553 0.9757 0.0318
-10.500 -0.1776 0.10923 0.10567 -0.0598 0.9650 0.0319
-10.000 -0.1369 0.10213 0.09854 -0.0643 0.9484 0.0335
-9.750 -0.1173 0.09844 0.09482 -0.0688 0.9394 0.0348
-9.500 -0.1042 0.09347 0.08982 -0.0778 0.9291 0.0374
-9.250 -0.0864 0.08814 0.08443 -0.0859 0.9184 0.0376
-9.000 -0.0672 0.08339 0.07963 -0.0921 0.9069 0.0376
-8.500 -0.0181 0.07756 0.07369 -0.0970 0.8865 0.0400
-8.250 -0.0225 0.07132 0.06739 -0.1044 0.8687 0.0381
-8.000 -0.0036 0.06966 0.06566 -0.1038 0.8582 0.0359
-7.750 -0.0023 0.06640 0.06236 -0.1053 0.8447 0.0347
-7.500 -0.0070 0.06230 0.05821 -0.1081 0.8319 0.0335
-7.250 -0.0029 0.05895 0.05482 -0.1107 0.8202 0.0338
-7.000 0.0049 0.05572 0.05153 -0.1133 0.8100 0.0347
-6.750 0.0122 0.05122 0.04691 -0.1172 0.8003 0.0350
-6.500 0.0199 0.04575 0.04128 -0.1212 0.7905 0.0345
-6.000 0.0416 0.03445 0.02930 -0.1264 0.7731 0.0352
-5.750 0.0551 0.02947 0.02373 -0.1271 0.7656 0.0360
-5.500 0.0718 0.02617 0.01993 -0.1267 0.7569 0.0363
-5.250 0.0921 0.02370 0.01694 -0.1261 0.7493 0.0368
-4.750 0.1375 0.02084 0.01337 -0.1249 0.7322 0.0385
-4.500 0.1614 0.01991 0.01227 -0.1242 0.7229 0.0390
-4.250 0.1865 0.01904 0.01117 -0.1237 0.7148 0.0395
-4.000 0.2112 0.01828 0.01023 -0.1231 0.7050 0.0400
-3.750 0.2366 0.01759 0.00935 -0.1225 0.6963 0.0406
-3.500 0.2620 0.01698 0.00859 -0.1219 0.6865 0.0414
-3.250 0.2877 0.01649 0.00794 -0.1213 0.6774 0.0426
-3.000 0.3134 0.01604 0.00733 -0.1207 0.6677 0.0437
-2.750 0.3390 0.01562 0.00678 -0.1201 0.6579 0.0443
-2.250 0.3895 0.01478 0.00586 -0.1188 0.6387 0.0460
-2.000 0.4149 0.01451 0.00553 -0.1182 0.6296 0.0472
-1.750 0.4403 0.01428 0.00524 -0.1176 0.6201 0.0485
-1.500 0.4658 0.01411 0.00500 -0.1171 0.6112 0.0505
-1.250 0.4912 0.01394 0.00477 -0.1165 0.6024 0.0529
-1.000 0.5167 0.01380 0.00460 -0.1159 0.5939 0.0556
-0.750 0.5423 0.01371 0.00443 -0.1153 0.5858 0.0590
-0.500 0.5680 0.01360 0.00430 -0.1148 0.5780 0.0645
-0.250 0.5935 0.01351 0.00420 -0.1142 0.5705 0.0768
0.000 0.6188 0.01337 0.00414 -0.1137 0.5636 0.1116
0.250 0.6432 0.01311 0.00417 -0.1132 0.5564 0.2081
0.500 0.6673 0.01292 0.00422 -0.1126 0.5502 0.3217
0.750 0.6895 0.01253 0.00434 -0.1116 0.5436 0.4955
1.000 0.7451 0.01170 0.00444 -0.1171 0.5362 1.0000
1.250 0.7700 0.01186 0.00449 -0.1164 0.5301 1.0000
1.500 0.7948 0.01202 0.00456 -0.1158 0.5238 1.0000
1.750 0.8195 0.01221 0.00462 -0.1151 0.5182 1.0000
2.000 0.8444 0.01237 0.00473 -0.1145 0.5123 1.0000
2.250 0.8690 0.01254 0.00483 -0.1138 0.5062 1.0000
2.500 0.8936 0.01275 0.00492 -0.1131 0.5008 1.0000
2.750 0.9182 0.01291 0.00507 -0.1125 0.4947 1.0000
3.000 0.9425 0.01310 0.00521 -0.1118 0.4886 1.0000
3.250 0.9669 0.01332 0.00533 -0.1111 0.4832 1.0000
3.500 0.9910 0.01349 0.00552 -0.1104 0.4767 1.0000
3.750 1.0149 0.01370 0.00567 -0.1097 0.4705 1.0000
4.000 1.0387 0.01391 0.00584 -0.1089 0.4647 1.0000
4.250 1.0622 0.01410 0.00604 -0.1082 0.4579 1.0000
4.500 1.0854 0.01433 0.00621 -0.1073 0.4518 1.0000
4.750 1.1085 0.01453 0.00643 -0.1065 0.4450 1.0000
5.000 1.1312 0.01475 0.00664 -0.1056 0.4383 1.0000
5.250 1.1537 0.01499 0.00686 -0.1047 0.4322 1.0000
5.500 1.1760 0.01522 0.00710 -0.1037 0.4252 1.0000
5.750 1.1978 0.01548 0.00734 -0.1027 0.4191 1.0000
6.000 1.2197 0.01572 0.00762 -0.1017 0.4124 1.0000
6.250 1.2408 0.01599 0.00788 -0.1006 0.4059 1.0000
6.500 1.2616 0.01627 0.00818 -0.0995 0.3993 1.0000
6.750 1.2819 0.01655 0.00849 -0.0982 0.3922 1.0000
7.000 1.3014 0.01687 0.00879 -0.0969 0.3861 1.0000
7.250 1.3211 0.01716 0.00914 -0.0956 0.3791 1.0000
7.500 1.3385 0.01751 0.00948 -0.0939 0.3721 1.0000
7.750 1.3554 0.01784 0.00986 -0.0921 0.3646 1.0000
8.000 1.3702 0.01822 0.01024 -0.0900 0.3572 1.0000
8.250 1.3855 0.01861 0.01067 -0.0881 0.3493 1.0000
8.500 1.3994 0.01906 0.01112 -0.0859 0.3417 1.0000
8.750 1.4138 0.01952 0.01162 -0.0839 0.3338 1.0000
9.000 1.4252 0.02007 0.01216 -0.0816 0.3250 1.0000
9.250 1.4395 0.02059 0.01274 -0.0798 0.3174 1.0000
9.500 1.4514 0.02121 0.01337 -0.0777 0.3103 1.0000
9.750 1.4646 0.02182 0.01404 -0.0758 0.3031 1.0000
10.000 1.4757 0.02253 0.01478 -0.0738 0.2960 1.0000
10.250 1.4874 0.02326 0.01556 -0.0720 0.2892 1.0000
10.500 1.4982 0.02406 0.01642 -0.0701 0.2823 1.0000
10.750 1.5079 0.02495 0.01735 -0.0683 0.2757 1.0000
11.000 1.5182 0.02585 0.01832 -0.0666 0.2689 1.0000
11.250 1.5260 0.02693 0.01941 -0.0647 0.2630 1.0000
11.500 1.5368 0.02789 0.02049 -0.0632 0.2567 1.0000
11.750 1.5436 0.02911 0.02175 -0.0615 0.2501 1.0000
12.000 1.5507 0.03036 0.02307 -0.0599 0.2427 1.0000
12.250 1.5555 0.03182 0.02457 -0.0583 0.2356 1.0000
12.500 1.5623 0.03320 0.02604 -0.0569 0.2297 1.0000
12.750 1.5680 0.03472 0.02764 -0.0556 0.2234 1.0000
13.000 1.5708 0.03649 0.02947 -0.0542 0.2169 1.0000
13.250 1.5735 0.03836 0.03142 -0.0530 0.2088 1.0000
13.500 1.5737 0.04050 0.03361 -0.0518 0.2005 1.0000
13.750 1.5700 0.04308 0.03622 -0.0506 0.1907 1.0000
14.000 1.5678 0.04569 0.03888 -0.0498 0.1798 1.0000
14.250 1.5634 0.04861 0.04185 -0.0490 0.1690 1.0000
14.500 1.5558 0.05201 0.04527 -0.0485 0.1562 1.0000
14.750 1.5477 0.05562 0.04891 -0.0481 0.1426 1.0000
15.000 1.5351 0.05992 0.05318 -0.0480 0.1253 1.0000
15.250 1.5176 0.06498 0.05818 -0.0483 0.1076 1.0000
15.500 1.5006 0.07018 0.06334 -0.0487 0.0967 1.0000
15.750 1.4855 0.07527 0.06844 -0.0494 0.0900 1.0000
16.000 1.4754 0.07985 0.07308 -0.0500 0.0856 1.0000
16.250 1.4647 0.08460 0.07791 -0.0509 0.0819 1.0000
16.500 1.4528 0.08963 0.08301 -0.0519 0.0787 1.0000
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