GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 50,000 Max Cl/Cd: 34.91 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe436-il-50000-n5.txt Download as CSV file: xf-goe436-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3339 0.10721 0.09990 -0.0322 1.0000 0.1408
-9.000 -0.3444 0.10555 0.09836 -0.0330 1.0000 0.1468
-8.750 -0.3676 0.10451 0.09751 -0.0344 1.0000 0.1484
-8.500 -0.3449 0.09971 0.09268 -0.0321 1.0000 0.1526
-8.250 -0.3423 0.09711 0.09014 -0.0310 1.0000 0.1563
-8.000 -0.3492 0.09489 0.08802 -0.0302 1.0000 0.1592
-7.750 -0.3630 0.09303 0.08630 -0.0291 1.0000 0.1612
-7.500 -0.4102 0.08486 0.07817 -0.0369 1.0000 0.1003
-7.250 -0.4064 0.08216 0.07551 -0.0343 1.0000 0.0982
-7.000 -0.4117 0.07921 0.07260 -0.0334 1.0000 0.0966
-6.750 -0.4183 0.07612 0.06952 -0.0330 1.0000 0.0961
-6.500 -0.4232 0.07293 0.06631 -0.0328 1.0000 0.0955
-6.250 -0.4261 0.06963 0.06296 -0.0328 1.0000 0.0954
-6.000 -0.4263 0.06623 0.05947 -0.0328 1.0000 0.0950
-5.750 -0.4239 0.06267 0.05577 -0.0329 1.0000 0.0938
-5.500 -0.4190 0.05897 0.05188 -0.0332 1.0000 0.0926
-5.250 -0.4012 0.05479 0.04739 -0.0358 0.9965 0.0917
-5.000 -0.3721 0.05120 0.04346 -0.0394 0.9893 0.0934
-4.750 -0.3414 0.04780 0.03965 -0.0429 0.9822 0.0955
-4.500 -0.3108 0.04458 0.03596 -0.0457 0.9748 0.0957
-4.250 -0.2804 0.04177 0.03268 -0.0479 0.9672 0.0962
-4.000 -0.2459 0.03937 0.02976 -0.0504 0.9602 0.0982
-3.750 -0.2139 0.03740 0.02717 -0.0519 0.9507 0.1008
-3.500 -0.1774 0.03546 0.02495 -0.0542 0.9409 0.1025
-3.250 -0.1368 0.03377 0.02302 -0.0569 0.9306 0.1043
-3.000 -0.1013 0.03247 0.02151 -0.0584 0.9179 0.1074
-2.750 -0.0648 0.03132 0.02009 -0.0600 0.9059 0.1121
-2.500 -0.0236 0.03012 0.01852 -0.0621 0.8968 0.1156
-2.250 0.0113 0.02904 0.01730 -0.0631 0.8858 0.1182
-2.000 0.0456 0.02819 0.01644 -0.0641 0.8747 0.1232
-1.750 0.0898 0.02733 0.01539 -0.0666 0.8666 0.1311
-1.500 0.1249 0.02655 0.01459 -0.0674 0.8549 0.1363
-1.250 0.1588 0.02588 0.01387 -0.0681 0.8429 0.1435
-1.000 0.1941 0.02520 0.01318 -0.0689 0.8315 0.1549
-0.750 0.2310 0.02447 0.01245 -0.0700 0.8207 0.1697
-0.500 0.2604 0.02387 0.01192 -0.0698 0.8065 0.1877
-0.250 0.2891 0.02307 0.01147 -0.0697 0.7921 0.2387
0.000 0.3625 0.02043 0.01100 -0.0770 0.7805 1.0000
0.250 0.3901 0.02041 0.01069 -0.0763 0.7637 1.0000
0.500 0.4170 0.02039 0.01044 -0.0756 0.7461 1.0000
0.750 0.4440 0.02037 0.01021 -0.0748 0.7280 1.0000
1.000 0.4716 0.02035 0.00999 -0.0742 0.7099 1.0000
1.250 0.4985 0.02037 0.00981 -0.0734 0.6915 1.0000
1.500 0.5243 0.02045 0.00972 -0.0725 0.6722 1.0000
1.750 0.5510 0.02054 0.00963 -0.0718 0.6536 1.0000
2.000 0.5777 0.02069 0.00960 -0.0711 0.6357 1.0000
2.250 0.6040 0.02090 0.00963 -0.0705 0.6185 1.0000
2.500 0.6296 0.02117 0.00976 -0.0698 0.6021 1.0000
2.750 0.6546 0.02149 0.00994 -0.0690 0.5863 1.0000
3.000 0.6793 0.02185 0.01019 -0.0683 0.5717 1.0000
3.250 0.7040 0.02223 0.01049 -0.0676 0.5582 1.0000
3.500 0.7293 0.02261 0.01076 -0.0670 0.5460 1.0000
3.750 0.7538 0.02303 0.01112 -0.0663 0.5343 1.0000
4.000 0.7773 0.02351 0.01159 -0.0655 0.5231 1.0000
4.250 0.8024 0.02395 0.01198 -0.0650 0.5135 1.0000
4.500 0.8268 0.02442 0.01244 -0.0644 0.5039 1.0000
4.750 0.8503 0.02496 0.01301 -0.0637 0.4948 1.0000
5.000 0.8761 0.02543 0.01344 -0.0632 0.4868 1.0000
5.250 0.8983 0.02606 0.01414 -0.0624 0.4783 1.0000
5.500 0.9243 0.02656 0.01463 -0.0620 0.4710 1.0000
5.750 0.9455 0.02726 0.01544 -0.0611 0.4628 1.0000
6.000 0.9711 0.02782 0.01600 -0.0607 0.4558 1.0000
6.250 0.9916 0.02858 0.01690 -0.0597 0.4479 1.0000
6.500 1.0160 0.02920 0.01756 -0.0592 0.4407 1.0000
6.750 1.0363 0.02999 0.01847 -0.0581 0.4329 1.0000
7.000 1.0593 0.03064 0.01919 -0.0574 0.4250 1.0000
7.250 1.0784 0.03146 0.02016 -0.0562 0.4168 1.0000
7.500 1.1010 0.03210 0.02086 -0.0553 0.4084 1.0000
7.750 1.1177 0.03300 0.02193 -0.0539 0.3998 1.0000
8.000 1.1414 0.03354 0.02251 -0.0531 0.3911 1.0000
8.250 1.1537 0.03450 0.02371 -0.0510 0.3812 1.0000
8.500 1.1746 0.03498 0.02424 -0.0498 0.3712 1.0000
8.750 1.1891 0.03565 0.02506 -0.0479 0.3603 1.0000
9.000 1.2001 0.03648 0.02607 -0.0457 0.3497 1.0000
9.250 1.2186 0.03691 0.02659 -0.0441 0.3395 1.0000
9.500 1.2279 0.03776 0.02764 -0.0417 0.3290 1.0000
9.750 1.2354 0.03864 0.02870 -0.0391 0.3185 1.0000
10.000 1.2496 0.03910 0.02924 -0.0372 0.3084 1.0000
10.250 1.2518 0.04018 0.03054 -0.0341 0.2978 1.0000
10.500 1.2516 0.04128 0.03181 -0.0308 0.2878 1.0000
10.750 1.2549 0.04204 0.03268 -0.0278 0.2770 1.0000
11.000 1.2512 0.04335 0.03415 -0.0247 0.2660 1.0000
11.250 1.2430 0.04532 0.03630 -0.0219 0.2552 1.0000
11.500 1.2388 0.04713 0.03825 -0.0197 0.2444 1.0000
11.750 1.2361 0.04893 0.04013 -0.0178 0.2332 1.0000
12.000 1.2278 0.05160 0.04296 -0.0164 0.2220 1.0000
12.250 1.2175 0.05481 0.04630 -0.0156 0.2106 1.0000
12.500 1.2099 0.05788 0.04945 -0.0150 0.1990 1.0000
12.750 1.2038 0.06095 0.05254 -0.0146 0.1871 1.0000
13.000 1.1988 0.06402 0.05558 -0.0145 0.1754 1.0000
13.250 1.1948 0.06704 0.05854 -0.0143 0.1641 1.0000
13.500 1.1833 0.07161 0.06320 -0.0151 0.1544 1.0000
13.750 1.1774 0.07541 0.06699 -0.0155 0.1458 1.0000
14.000 1.1770 0.07833 0.06983 -0.0154 0.1376 1.0000
14.250 1.1661 0.08342 0.07507 -0.0167 0.1311 1.0000
14.500 1.1667 0.08634 0.07793 -0.0169 0.1238 1.0000
14.750 1.1546 0.09191 0.08367 -0.0187 0.1183 1.0000
15.000 1.1469 0.09668 0.08853 -0.0203 0.1124 1.0000
15.250 1.1431 0.10068 0.09252 -0.0215 0.1064 1.0000
15.500 1.1249 0.10800 0.10006 -0.0248 0.1022 1.0000
15.750 1.1330 0.10947 0.10137 -0.0248 0.0953 1.0000
16.000 1.1087 0.11856 0.11076 -0.0293 0.0926 1.0000
16.250 1.0815 0.12877 0.12118 -0.0346 0.0902 1.0000
16.500 1.1013 0.12758 0.11986 -0.0332 0.0834 1.0000
16.750 1.0653 0.14059 0.13309 -0.0403 0.0822 1.0000
17.000 1.0176 0.15842 0.15094 -0.0502 0.0811 1.0000
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