GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 500,000 Max Cl/Cd: 102.33 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe533-il-500000-n5.txt Download as CSV file: xf-goe533-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3239 0.10814 0.10567 -0.0408 1.0000 0.0193
-11.500 -0.3183 0.10576 0.10330 -0.0414 1.0000 0.0195
-10.500 -0.4937 0.03833 0.03531 -0.1025 0.9500 0.0230
-10.250 -0.4673 0.03536 0.03213 -0.1088 0.9295 0.0232
-10.000 -0.4490 0.03242 0.02888 -0.1125 0.9003 0.0235
-9.750 -0.4356 0.03027 0.02642 -0.1132 0.8655 0.0237
-9.500 -0.4221 0.02866 0.02450 -0.1129 0.8305 0.0239
-9.250 -0.4092 0.02693 0.02242 -0.1122 0.7966 0.0242
-9.000 -0.3938 0.02538 0.02052 -0.1115 0.7669 0.0245
-8.750 -0.3763 0.02398 0.01880 -0.1109 0.7423 0.0250
-8.500 -0.3570 0.02268 0.01718 -0.1104 0.7218 0.0254
-8.250 -0.3365 0.02138 0.01556 -0.1099 0.7054 0.0258
-8.000 -0.3145 0.02030 0.01420 -0.1094 0.6913 0.0261
-7.750 -0.2911 0.01938 0.01303 -0.1090 0.6794 0.0264
-7.500 -0.2667 0.01864 0.01208 -0.1086 0.6694 0.0266
-7.250 -0.2427 0.01769 0.01097 -0.1083 0.6604 0.0268
-7.000 -0.2176 0.01698 0.01015 -0.1080 0.6528 0.0271
-6.750 -0.1919 0.01642 0.00952 -0.1078 0.6454 0.0274
-6.250 -0.1394 0.01558 0.00852 -0.1073 0.6328 0.0281
-6.000 -0.1129 0.01516 0.00803 -0.1071 0.6266 0.0286
-5.500 -0.0597 0.01431 0.00701 -0.1066 0.6156 0.0293
-5.250 -0.0328 0.01392 0.00655 -0.1064 0.6099 0.0297
-5.000 -0.0061 0.01356 0.00611 -0.1061 0.6043 0.0300
-4.750 0.0210 0.01322 0.00571 -0.1059 0.5993 0.0303
-4.500 0.0483 0.01290 0.00534 -0.1057 0.5937 0.0307
-4.250 0.0755 0.01263 0.00501 -0.1055 0.5885 0.0310
-4.000 0.1025 0.01234 0.00467 -0.1053 0.5839 0.0313
-3.750 0.1299 0.01198 0.00430 -0.1052 0.5792 0.0319
-3.500 0.1574 0.01175 0.00406 -0.1050 0.5738 0.0326
-3.250 0.1848 0.01157 0.00385 -0.1049 0.5686 0.0333
-3.000 0.2126 0.01139 0.00364 -0.1048 0.5639 0.0340
-2.750 0.2406 0.01120 0.00344 -0.1047 0.5588 0.0347
-2.500 0.2683 0.01106 0.00325 -0.1045 0.5531 0.0354
-2.250 0.2961 0.01094 0.00309 -0.1044 0.5477 0.0361
-2.000 0.3241 0.01078 0.00292 -0.1043 0.5416 0.0369
-1.750 0.3518 0.01065 0.00277 -0.1042 0.5355 0.0383
-1.500 0.3797 0.01057 0.00266 -0.1041 0.5300 0.0397
-1.250 0.4078 0.01049 0.00257 -0.1040 0.5235 0.0417
-1.000 0.4355 0.01043 0.00247 -0.1038 0.5166 0.0448
-0.750 0.4634 0.01035 0.00239 -0.1037 0.5093 0.0498
-0.500 0.4908 0.01018 0.00233 -0.1036 0.5014 0.0848
-0.250 0.5184 0.01006 0.00229 -0.1035 0.4934 0.1249
0.000 0.5449 0.00976 0.00225 -0.1035 0.4832 0.2332
0.250 0.5710 0.00934 0.00227 -0.1034 0.4724 0.4013
0.500 0.5978 0.00930 0.00234 -0.1032 0.4624 0.4684
0.750 0.6248 0.00930 0.00239 -0.1030 0.4535 0.5066
1.000 0.6515 0.00928 0.00248 -0.1027 0.4456 0.5534
1.250 0.6778 0.00927 0.00261 -0.1023 0.4371 0.6091
1.500 0.7045 0.00934 0.00271 -0.1019 0.4295 0.6413
1.750 0.7316 0.00943 0.00280 -0.1017 0.4218 0.6585
2.000 0.7583 0.00955 0.00289 -0.1014 0.4152 0.6738
2.250 0.7855 0.00963 0.00298 -0.1012 0.4086 0.6869
2.500 0.8121 0.00976 0.00307 -0.1009 0.4014 0.6976
2.750 0.8389 0.00986 0.00317 -0.1006 0.3941 0.7096
3.000 0.8651 0.00997 0.00329 -0.1002 0.3864 0.7241
3.250 0.8913 0.01007 0.00341 -0.0998 0.3799 0.7400
3.500 0.9174 0.01016 0.00353 -0.0995 0.3731 0.7556
3.750 0.9429 0.01029 0.00367 -0.0990 0.3669 0.7721
4.000 0.9686 0.01034 0.00380 -0.0985 0.3622 0.7959
4.250 0.9912 0.01026 0.00393 -0.0973 0.3571 0.8631
4.500 1.0267 0.01036 0.00408 -0.0990 0.3507 1.0000
4.750 1.0531 0.01052 0.00423 -0.0987 0.3454 1.0000
5.000 1.0792 0.01071 0.00439 -0.0984 0.3396 1.0000
5.250 1.1046 0.01093 0.00458 -0.0980 0.3341 1.0000
5.500 1.1306 0.01111 0.00476 -0.0977 0.3294 1.0000
5.750 1.1559 0.01132 0.00495 -0.0973 0.3220 1.0000
6.000 1.1804 0.01157 0.00517 -0.0968 0.3144 1.0000
6.250 1.2055 0.01179 0.00537 -0.0964 0.3071 1.0000
6.500 1.2296 0.01205 0.00561 -0.0958 0.3010 1.0000
6.750 1.2545 0.01226 0.00584 -0.0954 0.2949 1.0000
7.000 1.2777 0.01256 0.00610 -0.0947 0.2858 1.0000
7.250 1.3012 0.01283 0.00636 -0.0940 0.2764 1.0000
7.500 1.3237 0.01315 0.00665 -0.0932 0.2675 1.0000
7.750 1.3462 0.01346 0.00695 -0.0924 0.2578 1.0000
8.000 1.3676 0.01381 0.00727 -0.0915 0.2470 1.0000
8.250 1.3874 0.01424 0.00765 -0.0903 0.2333 1.0000
8.500 1.4043 0.01481 0.00812 -0.0887 0.2144 1.0000
8.750 1.4195 0.01542 0.00864 -0.0868 0.1983 1.0000
9.000 1.4341 0.01593 0.00912 -0.0848 0.1885 1.0000
9.250 1.4477 0.01646 0.00964 -0.0826 0.1813 1.0000
9.500 1.4624 0.01695 0.01014 -0.0806 0.1760 1.0000
9.750 1.4757 0.01751 0.01070 -0.0785 0.1711 1.0000
10.000 1.4892 0.01807 0.01129 -0.0766 0.1671 1.0000
10.250 1.5038 0.01860 0.01187 -0.0748 0.1636 1.0000
10.500 1.5162 0.01925 0.01254 -0.0728 0.1592 1.0000
10.750 1.5254 0.02010 0.01339 -0.0706 0.1540 1.0000
11.000 1.5383 0.02078 0.01413 -0.0690 0.1487 1.0000
11.250 1.5466 0.02176 0.01510 -0.0669 0.1410 1.0000
11.500 1.5563 0.02272 0.01610 -0.0652 0.1335 1.0000
11.750 1.5616 0.02401 0.01736 -0.0632 0.1198 1.0000
12.000 1.5504 0.02657 0.01972 -0.0603 0.0893 1.0000
12.250 1.5438 0.02907 0.02217 -0.0583 0.0773 1.0000
12.500 1.5431 0.03129 0.02442 -0.0569 0.0718 1.0000
12.750 1.5461 0.03331 0.02651 -0.0560 0.0686 1.0000
13.000 1.5475 0.03557 0.02883 -0.0551 0.0654 1.0000
13.250 1.5462 0.03820 0.03151 -0.0544 0.0623 1.0000
13.500 1.5482 0.04056 0.03394 -0.0539 0.0603 1.0000
13.750 1.5504 0.04297 0.03643 -0.0536 0.0585 1.0000
14.000 1.5502 0.04567 0.03920 -0.0532 0.0565 1.0000
14.250 1.5488 0.04856 0.04216 -0.0530 0.0548 1.0000
14.500 1.5455 0.05175 0.04541 -0.0529 0.0531 1.0000
14.750 1.5451 0.05469 0.04845 -0.0530 0.0519 1.0000
15.000 1.5455 0.05759 0.05144 -0.0531 0.0507 1.0000
15.250 1.5448 0.06071 0.05465 -0.0533 0.0493 1.0000
15.500 1.5426 0.06410 0.05811 -0.0537 0.0478 1.0000
15.750 1.5390 0.06775 0.06184 -0.0543 0.0464 1.0000
16.000 1.5333 0.07180 0.06595 -0.0550 0.0449 1.0000
16.250 1.5327 0.07522 0.06947 -0.0557 0.0436 1.0000
16.500 1.5309 0.07888 0.07322 -0.0565 0.0420 1.0000
16.750 1.5271 0.08288 0.07730 -0.0575 0.0402 1.0000
17.000 1.5219 0.08716 0.08165 -0.0586 0.0387 1.0000
17.250 1.5189 0.09118 0.08575 -0.0598 0.0370 1.0000
17.500 1.5150 0.09537 0.09003 -0.0611 0.0348 1.0000
17.750 1.5085 0.10003 0.09474 -0.0626 0.0328 1.0000
18.000 1.5037 0.10445 0.09925 -0.0641 0.0302 1.0000
18.250 1.4972 0.10923 0.10407 -0.0659 0.0274 1.0000
18.500 1.4905 0.11407 0.10897 -0.0678 0.0248 1.0000
18.750 1.4822 0.11924 0.11420 -0.0699 0.0224 1.0000
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