GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 200,000 Max Cl/Cd: 76.06 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe187-il-200000-n5.txt Download as CSV file: xf-goe187-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2934 0.09803 0.09485 -0.0262 1.0000 0.0130
-7.500 -0.2918 0.09580 0.09268 -0.0273 1.0000 0.0131
-7.250 -0.2876 0.09332 0.09026 -0.0289 1.0000 0.0131
-7.000 -0.2801 0.09054 0.08753 -0.0311 0.9983 0.0132
-6.750 -0.2528 0.08612 0.08309 -0.0384 0.9886 0.0133
-6.500 -0.2254 0.08171 0.07865 -0.0453 0.9772 0.0133
-6.250 -0.1979 0.07738 0.07427 -0.0516 0.9644 0.0134
-6.000 -0.1694 0.07305 0.06986 -0.0576 0.9514 0.0134
-5.750 -0.1401 0.06877 0.06550 -0.0631 0.9377 0.0134
-5.500 -0.1109 0.06462 0.06122 -0.0680 0.9218 0.0135
-5.250 -0.0899 0.05835 0.05488 -0.0722 0.9043 0.0139
-5.000 -0.0709 0.05369 0.05011 -0.0745 0.8849 0.0144
-4.750 -0.0525 0.05027 0.04658 -0.0757 0.8628 0.0150
-4.500 -0.0320 0.04729 0.04345 -0.0770 0.8414 0.0161
-4.250 -0.0075 0.04437 0.04033 -0.0787 0.8215 0.0175
-4.000 0.0195 0.04142 0.03717 -0.0805 0.8046 0.0190
-3.750 0.0481 0.03854 0.03404 -0.0821 0.7904 0.0205
-3.500 0.0792 0.03603 0.03123 -0.0833 0.7776 0.0229
-3.250 0.1150 0.03480 0.02954 -0.0837 0.7656 0.0245
-3.000 0.1438 0.03274 0.02714 -0.0839 0.7544 0.0247
-2.750 0.1720 0.03060 0.02468 -0.0842 0.7433 0.0247
-2.250 0.2239 0.02430 0.01797 -0.0853 0.7231 0.0217
-2.000 0.2556 0.02174 0.01492 -0.0847 0.7136 0.0155
-1.750 0.2855 0.02006 0.01286 -0.0843 0.7039 0.0151
-1.500 0.3129 0.01899 0.01158 -0.0844 0.6945 0.0175
-1.250 0.3423 0.01761 0.00985 -0.0840 0.6847 0.0170
-1.000 0.3714 0.01638 0.00833 -0.0835 0.6748 0.0166
-0.750 0.3998 0.01538 0.00708 -0.0831 0.6647 0.0169
-0.500 0.4277 0.01464 0.00614 -0.0827 0.6542 0.0187
-0.250 0.4555 0.01401 0.00538 -0.0824 0.6434 0.0215
0.000 0.4830 0.01339 0.00466 -0.0820 0.6327 0.0231
0.250 0.5102 0.01289 0.00409 -0.0818 0.6216 0.0274
0.500 0.5376 0.01258 0.00367 -0.0817 0.6093 0.0320
0.750 0.5651 0.01237 0.00333 -0.0816 0.5957 0.0411
1.000 0.5925 0.01225 0.00307 -0.0814 0.5811 0.0522
1.250 0.6212 0.01013 0.00301 -0.0818 0.5659 1.0000
1.500 0.6482 0.01027 0.00294 -0.0816 0.5494 1.0000
1.750 0.6751 0.01042 0.00293 -0.0814 0.5319 1.0000
2.000 0.7017 0.01060 0.00294 -0.0812 0.5131 1.0000
2.250 0.7279 0.01082 0.00297 -0.0809 0.4933 1.0000
2.500 0.7540 0.01106 0.00305 -0.0807 0.4725 1.0000
2.750 0.7798 0.01133 0.00315 -0.0804 0.4532 1.0000
3.000 0.8056 0.01162 0.00329 -0.0801 0.4364 1.0000
3.250 0.8315 0.01190 0.00346 -0.0799 0.4219 1.0000
3.500 0.8576 0.01216 0.00364 -0.0797 0.4098 1.0000
3.750 0.8838 0.01241 0.00383 -0.0795 0.3995 1.0000
4.000 0.9098 0.01268 0.00407 -0.0793 0.3904 1.0000
4.250 0.9359 0.01292 0.00429 -0.0792 0.3814 1.0000
4.500 0.9620 0.01318 0.00454 -0.0790 0.3734 1.0000
4.750 0.9879 0.01343 0.00482 -0.0788 0.3655 1.0000
5.000 1.0139 0.01369 0.00509 -0.0786 0.3584 1.0000
5.250 1.0397 0.01395 0.00538 -0.0784 0.3510 1.0000
5.500 1.0654 0.01422 0.00569 -0.0782 0.3435 1.0000
5.750 1.0908 0.01449 0.00603 -0.0780 0.3356 1.0000
6.000 1.1162 0.01477 0.00637 -0.0777 0.3260 1.0000
6.250 1.1411 0.01508 0.00673 -0.0774 0.3170 1.0000
6.500 1.1664 0.01535 0.00713 -0.0772 0.3081 1.0000
6.750 1.1911 0.01566 0.00753 -0.0768 0.2978 1.0000
7.000 1.2155 0.01599 0.00795 -0.0764 0.2858 1.0000
7.250 1.2392 0.01636 0.00839 -0.0759 0.2662 1.0000
7.500 1.2546 0.01746 0.00903 -0.0746 0.1876 1.0000
7.750 1.2680 0.01891 0.01016 -0.0730 0.1353 1.0000
8.000 1.2804 0.02041 0.01130 -0.0713 0.0891 1.0000
8.250 1.2959 0.02151 0.01232 -0.0698 0.0633 1.0000
8.500 1.3002 0.02362 0.01409 -0.0668 0.0139 1.0000
8.750 1.3146 0.02467 0.01534 -0.0650 0.0112 1.0000
9.000 1.3252 0.02598 0.01685 -0.0628 0.0093 1.0000
9.250 1.3316 0.02751 0.01862 -0.0600 0.0083 1.0000
9.500 1.3382 0.02875 0.02005 -0.0572 0.0079 1.0000
9.750 1.3426 0.03023 0.02173 -0.0544 0.0075 1.0000
10.000 1.3455 0.03192 0.02366 -0.0519 0.0070 1.0000
10.250 1.3469 0.03384 0.02575 -0.0497 0.0065 1.0000
10.500 1.3455 0.03616 0.02821 -0.0479 0.0060 1.0000
10.750 1.3386 0.03920 0.03142 -0.0464 0.0057 1.0000
11.000 1.3339 0.04230 0.03467 -0.0454 0.0055 1.0000
11.250 1.3308 0.04542 0.03795 -0.0447 0.0054 1.0000
11.500 1.3267 0.04878 0.04146 -0.0443 0.0053 1.0000
11.750 1.3220 0.05232 0.04514 -0.0441 0.0052 1.0000
12.000 1.3174 0.05593 0.04888 -0.0439 0.0051 1.0000
12.250 1.3129 0.05956 0.05264 -0.0438 0.0050 1.0000
12.500 1.3089 0.06315 0.05635 -0.0436 0.0049 1.0000
12.750 1.3055 0.06671 0.06004 -0.0435 0.0048 1.0000
13.000 1.3026 0.07020 0.06365 -0.0432 0.0047 1.0000
13.250 1.3004 0.07368 0.06727 -0.0431 0.0047 1.0000
13.500 1.2985 0.07720 0.07092 -0.0429 0.0046 1.0000
13.750 1.2965 0.08081 0.07467 -0.0428 0.0045 1.0000
14.000 1.2939 0.08465 0.07866 -0.0431 0.0044 1.0000
14.250 1.2903 0.08874 0.08290 -0.0438 0.0043 1.0000
14.500 1.2859 0.09303 0.08733 -0.0448 0.0042 1.0000
14.750 1.2818 0.09727 0.09168 -0.0459 0.0040 1.0000
15.000 1.2762 0.10189 0.09643 -0.0473 0.0039 1.0000
15.250 1.2703 0.10657 0.10122 -0.0486 0.0038 1.0000
15.500 1.2616 0.11206 0.10687 -0.0506 0.0037 1.0000
15.750 1.2510 0.11841 0.11344 -0.0540 0.0037 1.0000
16.000 1.2408 0.12483 0.12008 -0.0574 0.0036 1.0000
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Polar data table (+)
Polar graphs
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