GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 200,000 Max Cl/Cd: 71.05 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe188-il-200000.txt Download as CSV file: xf-goe188-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3837 0.09198 0.08869 -0.0167 1.0000 0.0194
-7.500 -0.3808 0.08875 0.08551 -0.0183 1.0000 0.0197
-7.250 -0.3779 0.08547 0.08227 -0.0205 1.0000 0.0200
-7.000 -0.3714 0.08186 0.07869 -0.0236 1.0000 0.0203
-6.750 -0.3636 0.07818 0.07504 -0.0268 1.0000 0.0207
-6.500 -0.3547 0.07452 0.07139 -0.0297 1.0000 0.0211
-6.250 -0.3453 0.07092 0.06780 -0.0322 1.0000 0.0216
-6.000 -0.3357 0.06747 0.06435 -0.0342 1.0000 0.0221
-5.750 -0.3269 0.06430 0.06117 -0.0354 1.0000 0.0227
-5.500 -0.3328 0.06259 0.05949 -0.0332 1.0000 0.0230
-5.250 -0.2799 0.05827 0.05484 -0.0426 0.9927 0.0247
-5.000 -0.2345 0.05496 0.05115 -0.0487 0.9852 0.0252
-4.750 -0.2105 0.04717 0.04334 -0.0535 0.9768 0.0265
-4.500 -0.1777 0.04311 0.03922 -0.0578 0.9704 0.0284
-4.250 -0.1414 0.03964 0.03553 -0.0614 0.9591 0.0313
-4.000 -0.0946 0.03809 0.03326 -0.0639 0.9457 0.0371
-3.750 -0.0687 0.03297 0.02825 -0.0668 0.9308 0.0409
-3.500 -0.0369 0.03084 0.02583 -0.0677 0.9136 0.0466
-3.250 -0.0078 0.02848 0.02302 -0.0678 0.8971 0.0526
-3.000 0.0169 0.02656 0.02096 -0.0678 0.8821 0.0588
-2.750 0.0428 0.02476 0.01884 -0.0675 0.8684 0.0690
-2.500 0.0679 0.02326 0.01710 -0.0672 0.8556 0.0837
-2.250 0.0923 0.02196 0.01557 -0.0670 0.8437 0.1107
-1.250 0.2103 0.01711 0.00949 -0.0632 0.8009 0.0754
-1.000 0.2397 0.01595 0.00812 -0.0621 0.7906 0.0595
-0.750 0.2685 0.01531 0.00728 -0.0611 0.7804 0.0486
-0.500 0.2955 0.01429 0.00620 -0.0603 0.7707 0.0449
-0.250 0.3223 0.01362 0.00547 -0.0596 0.7607 0.0430
0.000 0.3493 0.01308 0.00491 -0.0592 0.7497 0.0432
0.250 0.3765 0.01276 0.00451 -0.0589 0.7391 0.0481
0.500 0.4039 0.01249 0.00408 -0.0585 0.7287 0.0520
0.750 0.4315 0.01226 0.00375 -0.0580 0.7176 0.0678
1.000 0.4606 0.00979 0.00363 -0.0579 0.7054 1.0000
1.250 0.4873 0.00987 0.00352 -0.0575 0.6927 1.0000
1.500 0.5139 0.00995 0.00345 -0.0571 0.6795 1.0000
1.750 0.5404 0.01004 0.00341 -0.0567 0.6652 1.0000
2.000 0.5669 0.01014 0.00338 -0.0563 0.6498 1.0000
2.250 0.5934 0.01026 0.00338 -0.0560 0.6337 1.0000
2.500 0.6199 0.01039 0.00341 -0.0556 0.6161 1.0000
2.750 0.6463 0.01052 0.00346 -0.0553 0.5961 1.0000
3.000 0.6725 0.01068 0.00348 -0.0549 0.5759 1.0000
3.250 0.6987 0.01083 0.00355 -0.0546 0.5526 1.0000
3.500 0.7248 0.01102 0.00364 -0.0542 0.5307 1.0000
3.750 0.7509 0.01123 0.00375 -0.0540 0.5095 1.0000
4.000 0.7770 0.01150 0.00390 -0.0537 0.4924 1.0000
4.250 0.8031 0.01179 0.00410 -0.0535 0.4769 1.0000
4.500 0.8293 0.01210 0.00437 -0.0533 0.4629 1.0000
4.750 0.8555 0.01243 0.00465 -0.0531 0.4503 1.0000
5.000 0.8819 0.01275 0.00496 -0.0530 0.4388 1.0000
5.250 0.9082 0.01309 0.00530 -0.0529 0.4283 1.0000
5.500 0.9344 0.01348 0.00569 -0.0528 0.4188 1.0000
5.750 0.9606 0.01384 0.00607 -0.0526 0.4090 1.0000
6.000 0.9865 0.01418 0.00646 -0.0525 0.3981 1.0000
6.250 1.0118 0.01450 0.00681 -0.0522 0.3851 1.0000
6.500 1.0368 0.01480 0.00718 -0.0519 0.3712 1.0000
6.750 1.0618 0.01511 0.00754 -0.0516 0.3582 1.0000
7.000 1.0866 0.01543 0.00792 -0.0512 0.3458 1.0000
7.250 1.1112 0.01573 0.00830 -0.0509 0.3323 1.0000
7.500 1.1356 0.01604 0.00872 -0.0505 0.3191 1.0000
7.750 1.1597 0.01636 0.00914 -0.0500 0.3056 1.0000
8.000 1.1836 0.01668 0.00959 -0.0496 0.2911 1.0000
8.250 1.2072 0.01699 0.01004 -0.0491 0.2742 1.0000
8.500 1.2296 0.01733 0.01048 -0.0484 0.2498 1.0000
8.750 1.2492 0.01792 0.01098 -0.0475 0.2055 1.0000
9.000 1.2630 0.01924 0.01198 -0.0460 0.1498 1.0000
9.250 1.2740 0.02091 0.01330 -0.0443 0.0976 1.0000
9.500 1.2857 0.02242 0.01473 -0.0425 0.0783 1.0000
9.750 1.2963 0.02393 0.01626 -0.0405 0.0636 1.0000
10.000 1.2994 0.02596 0.01827 -0.0378 0.0482 1.0000
10.250 1.2976 0.02815 0.02052 -0.0343 0.0368 1.0000
10.500 1.3004 0.02971 0.02222 -0.0312 0.0311 1.0000
10.750 1.2930 0.03220 0.02474 -0.0280 0.0281 1.0000
11.000 1.2973 0.03403 0.02674 -0.0262 0.0254 1.0000
11.250 1.3002 0.03610 0.02894 -0.0247 0.0232 1.0000
11.500 1.3006 0.03855 0.03149 -0.0235 0.0219 1.0000
11.750 1.2979 0.04148 0.03449 -0.0223 0.0208 1.0000
12.000 1.2943 0.04485 0.03793 -0.0203 0.0199 1.0000
12.250 1.2985 0.04738 0.04066 -0.0191 0.0193 1.0000
12.500 1.3018 0.05014 0.04362 -0.0179 0.0188 1.0000
12.750 1.3037 0.05310 0.04679 -0.0170 0.0183 1.0000
13.000 1.3036 0.05623 0.05012 -0.0165 0.0176 1.0000
13.250 1.3018 0.05949 0.05357 -0.0164 0.0168 1.0000
13.500 1.2979 0.06307 0.05733 -0.0166 0.0162 1.0000
13.750 1.2925 0.06693 0.06140 -0.0171 0.0158 1.0000
14.000 1.2850 0.07131 0.06600 -0.0176 0.0156 1.0000
14.250 1.2753 0.07607 0.07097 -0.0185 0.0155 1.0000
14.500 1.2632 0.08134 0.07647 -0.0199 0.0154 1.0000
14.750 1.2490 0.08710 0.08247 -0.0219 0.0155 1.0000
15.000 1.2329 0.09352 0.08911 -0.0245 0.0155 1.0000
15.250 1.2157 0.10048 0.09630 -0.0278 0.0156 1.0000
15.500 1.1972 0.10809 0.10413 -0.0317 0.0158 1.0000
15.750 1.1749 0.11702 0.11329 -0.0369 0.0161 1.0000
16.000 1.1519 0.12664 0.12309 -0.0428 0.0164 1.0000
16.250 1.1280 0.13710 0.13373 -0.0494 0.0168 1.0000
16.500 1.1031 0.14869 0.14547 -0.0568 0.0173 1.0000
16.750 1.0757 0.16208 0.15897 -0.0652 0.0183 1.0000
17.000 1.0540 0.17448 0.17138 -0.0722 0.0194 1.0000
17.250 1.0428 0.18399 0.18089 -0.0771 0.0200 1.0000
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Polar data table (+)
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