GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.89 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe187-il-1000000.txt Download as CSV file: xf-goe187-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3589 0.09401 0.09251 -0.0137 1.0000 0.0062
-7.750 -0.3545 0.09075 0.08927 -0.0158 1.0000 0.0063
-7.500 -0.3511 0.08749 0.08604 -0.0182 1.0000 0.0063
-7.250 -0.2538 0.06615 0.06480 -0.0285 0.9773 0.0066
-7.000 -0.2462 0.06215 0.06075 -0.0314 0.9340 0.0067
-6.750 -0.2424 0.05875 0.05722 -0.0333 0.8949 0.0068
-6.500 -0.2349 0.05499 0.05334 -0.0362 0.8648 0.0069
-6.250 -0.2244 0.05109 0.04934 -0.0396 0.8398 0.0070
-6.000 -0.2114 0.04707 0.04520 -0.0431 0.8169 0.0072
-5.750 -0.1960 0.04301 0.04104 -0.0465 0.7967 0.0075
-5.500 -0.1784 0.03900 0.03691 -0.0498 0.7785 0.0078
-5.250 -0.1588 0.03496 0.03274 -0.0529 0.7629 0.0082
-0.750 0.3178 0.00981 0.00370 -0.0637 0.6117 0.0139
-0.500 0.3458 0.00948 0.00332 -0.0637 0.5990 0.0152
-0.250 0.3737 0.00912 0.00288 -0.0636 0.5829 0.0161
0.000 0.4017 0.00899 0.00266 -0.0636 0.5625 0.0179
0.250 0.4295 0.00883 0.00238 -0.0635 0.5389 0.0188
0.500 0.4570 0.00837 0.00179 -0.0634 0.5136 0.0215
0.750 0.4847 0.00840 0.00169 -0.0634 0.4827 0.0246
1.000 0.5121 0.00853 0.00167 -0.0634 0.4514 0.0272
1.250 0.5398 0.00848 0.00147 -0.0634 0.4298 0.0337
1.500 0.5677 0.00854 0.00144 -0.0634 0.4137 0.0406
1.750 0.5959 0.00646 0.00158 -0.0643 0.4003 1.0000
2.000 0.6235 0.00660 0.00162 -0.0643 0.3889 1.0000
2.250 0.6513 0.00672 0.00166 -0.0643 0.3796 1.0000
2.500 0.6790 0.00684 0.00172 -0.0643 0.3711 1.0000
3.000 0.7344 0.00709 0.00186 -0.0644 0.3553 1.0000
3.250 0.7620 0.00722 0.00195 -0.0644 0.3482 1.0000
3.500 0.7897 0.00733 0.00203 -0.0645 0.3419 1.0000
3.750 0.8172 0.00747 0.00214 -0.0645 0.3346 1.0000
4.000 0.8449 0.00759 0.00224 -0.0645 0.3279 1.0000
4.250 0.8723 0.00774 0.00235 -0.0646 0.3201 1.0000
4.500 0.8998 0.00786 0.00246 -0.0646 0.3130 1.0000
4.750 0.9271 0.00803 0.00260 -0.0646 0.3040 1.0000
5.000 0.9545 0.00816 0.00273 -0.0647 0.2956 1.0000
5.250 0.9817 0.00832 0.00287 -0.0647 0.2871 1.0000
5.500 1.0087 0.00851 0.00302 -0.0647 0.2763 1.0000
5.750 1.0355 0.00871 0.00320 -0.0647 0.2623 1.0000
6.000 1.0608 0.00912 0.00344 -0.0645 0.2249 1.0000
6.250 1.0826 0.01004 0.00399 -0.0639 0.1609 1.0000
6.500 1.1070 0.01056 0.00439 -0.0636 0.1331 1.0000
6.750 1.1302 0.01123 0.00485 -0.0632 0.0990 1.0000
7.000 1.1554 0.01161 0.00520 -0.0629 0.0901 1.0000
7.250 1.1803 0.01199 0.00556 -0.0627 0.0842 1.0000
7.500 1.2054 0.01235 0.00592 -0.0625 0.0783 1.0000
7.750 1.2311 0.01259 0.00621 -0.0623 0.0738 1.0000
8.000 1.2552 0.01303 0.00659 -0.0620 0.0590 1.0000
8.250 1.2711 0.01451 0.00776 -0.0605 0.0125 1.0000
8.500 1.2935 0.01513 0.00844 -0.0598 0.0102 1.0000
8.750 1.3142 0.01593 0.00936 -0.0588 0.0084 1.0000
9.000 1.3365 0.01646 0.00998 -0.0582 0.0079 1.0000
9.250 1.3576 0.01711 0.01070 -0.0574 0.0072 1.0000
9.500 1.3777 0.01783 0.01149 -0.0564 0.0066 1.0000
9.750 1.3960 0.01868 0.01243 -0.0552 0.0061 1.0000
10.000 1.4045 0.02042 0.01436 -0.0527 0.0054 1.0000
10.250 1.4225 0.02113 0.01514 -0.0515 0.0052 1.0000
10.500 1.4384 0.02197 0.01606 -0.0500 0.0049 1.0000
10.750 1.4507 0.02300 0.01721 -0.0481 0.0046 1.0000
11.000 1.4592 0.02411 0.01842 -0.0456 0.0044 1.0000
11.250 1.4631 0.02532 0.01972 -0.0425 0.0043 1.0000
11.500 1.4666 0.02669 0.02119 -0.0398 0.0041 1.0000
11.750 1.4693 0.02828 0.02289 -0.0376 0.0040 1.0000
12.000 1.4716 0.03010 0.02481 -0.0358 0.0039 1.0000
12.250 1.4730 0.03221 0.02701 -0.0345 0.0037 1.0000
12.500 1.4720 0.03476 0.02967 -0.0336 0.0036 1.0000
12.750 1.4678 0.03788 0.03290 -0.0330 0.0035 1.0000
13.000 1.4603 0.04160 0.03675 -0.0328 0.0035 1.0000
13.250 1.4484 0.04596 0.04125 -0.0328 0.0034 1.0000
13.500 1.4338 0.05072 0.04615 -0.0328 0.0033 1.0000
13.750 1.4155 0.05589 0.05146 -0.0325 0.0032 1.0000
14.000 1.4093 0.05990 0.05560 -0.0330 0.0032 1.0000
14.250 1.4054 0.06377 0.05960 -0.0340 0.0032 1.0000
14.500 1.3993 0.06800 0.06396 -0.0350 0.0031 1.0000
14.750 1.3931 0.07244 0.06852 -0.0363 0.0031 1.0000
15.000 1.3852 0.07721 0.07342 -0.0377 0.0030 1.0000
15.250 1.3765 0.08224 0.07858 -0.0392 0.0030 1.0000
15.500 1.3673 0.08748 0.08394 -0.0410 0.0030 1.0000
15.750 1.3575 0.09291 0.08950 -0.0430 0.0029 1.0000
16.000 1.3474 0.09854 0.09525 -0.0451 0.0029 1.0000
16.250 1.3370 0.10436 0.10119 -0.0475 0.0028 1.0000
16.500 1.3263 0.11030 0.10725 -0.0500 0.0028 1.0000
16.750 1.3144 0.11654 0.11362 -0.0527 0.0028 1.0000
17.000 1.3031 0.12287 0.12007 -0.0556 0.0028 1.0000
17.250 1.2911 0.12947 0.12679 -0.0588 0.0028 1.0000
17.500 1.2801 0.13604 0.13348 -0.0621 0.0027 1.0000
17.750 1.2683 0.14294 0.14050 -0.0657 0.0027 1.0000
18.000 1.2565 0.15008 0.14776 -0.0695 0.0027 1.0000
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Polar data table (+)
Polar graphs
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