GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 100,000 Max Cl/Cd: 51.41 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe188-il-100000.txt Download as CSV file: xf-goe188-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3902 0.09902 0.09438 -0.0168 1.0000 0.0477
-7.750 -0.3898 0.09635 0.09178 -0.0201 1.0000 0.0486
-7.500 -0.3873 0.09354 0.08903 -0.0258 1.0000 0.0493
-7.250 -0.3799 0.09060 0.08608 -0.0324 1.0000 0.0497
-7.000 -0.3711 0.08782 0.08322 -0.0371 1.0000 0.0500
-6.750 -0.3659 0.08168 0.07721 -0.0360 1.0000 0.0510
-6.500 -0.3600 0.07758 0.07323 -0.0319 1.0000 0.0532
-6.250 -0.3518 0.07430 0.06998 -0.0323 1.0000 0.0555
-6.000 -0.3429 0.07106 0.06675 -0.0339 1.0000 0.0586
-5.750 -0.3301 0.06829 0.06388 -0.0377 1.0000 0.0627
-5.500 -0.3185 0.06716 0.06239 -0.0410 1.0000 0.0645
-5.250 -0.3224 0.06195 0.05758 -0.0369 1.0000 0.0671
-5.000 -0.3261 0.06015 0.05584 -0.0339 1.0000 0.0700
-4.750 -0.3269 0.05850 0.05416 -0.0322 1.0000 0.0739
-4.500 -0.3165 0.05744 0.05267 -0.0337 1.0000 0.0793
-4.250 -0.3087 0.05338 0.04885 -0.0328 0.9984 0.0832
-4.000 -0.2670 0.04927 0.04444 -0.0390 0.9916 0.0963
-3.750 -0.2282 0.04551 0.04052 -0.0439 0.9851 0.1129
-3.500 -0.1888 0.04209 0.03687 -0.0488 0.9766 0.1397
-3.250 -0.1488 0.03878 0.03347 -0.0534 0.9687 0.1827
-2.250 -0.0215 0.02784 0.02316 -0.0566 0.9342 0.4796
-2.000 0.0996 0.02574 0.01797 -0.0716 0.9283 0.1503
-1.750 0.1441 0.02341 0.01517 -0.0722 0.9191 0.1037
-1.500 0.1845 0.02178 0.01315 -0.0727 0.9094 0.0826
-1.250 0.2242 0.02047 0.01163 -0.0735 0.9006 0.0739
-1.000 0.2573 0.01935 0.01037 -0.0734 0.8893 0.0691
-0.750 0.2869 0.01848 0.00948 -0.0728 0.8771 0.0682
-0.500 0.3144 0.01778 0.00878 -0.0721 0.8647 0.0733
-0.250 0.3413 0.01730 0.00818 -0.0711 0.8520 0.0760
0.000 0.3683 0.01692 0.00764 -0.0702 0.8392 0.0813
0.250 0.3950 0.01660 0.00727 -0.0692 0.8261 0.1019
0.500 0.4294 0.01417 0.00701 -0.0691 0.8139 1.0000
0.750 0.4542 0.01434 0.00687 -0.0679 0.7994 1.0000
1.000 0.4786 0.01452 0.00681 -0.0667 0.7842 1.0000
1.250 0.5031 0.01469 0.00680 -0.0656 0.7687 1.0000
1.500 0.5276 0.01484 0.00679 -0.0646 0.7527 1.0000
1.750 0.5524 0.01498 0.00678 -0.0635 0.7364 1.0000
2.000 0.5774 0.01510 0.00676 -0.0625 0.7199 1.0000
2.250 0.6026 0.01521 0.00673 -0.0615 0.7035 1.0000
2.500 0.6275 0.01537 0.00682 -0.0606 0.6845 1.0000
2.750 0.6528 0.01553 0.00687 -0.0598 0.6660 1.0000
3.000 0.6785 0.01569 0.00691 -0.0590 0.6486 1.0000
3.250 0.7042 0.01590 0.00701 -0.0583 0.6314 1.0000
3.500 0.7297 0.01617 0.00726 -0.0577 0.6129 1.0000
3.750 0.7554 0.01643 0.00745 -0.0572 0.5958 1.0000
4.000 0.7812 0.01666 0.00761 -0.0566 0.5793 1.0000
4.250 0.8069 0.01687 0.00775 -0.0561 0.5631 1.0000
4.500 0.8328 0.01711 0.00797 -0.0556 0.5478 1.0000
4.750 0.8587 0.01741 0.00824 -0.0552 0.5335 1.0000
5.000 0.8846 0.01775 0.00860 -0.0548 0.5200 1.0000
5.250 0.9104 0.01812 0.00900 -0.0545 0.5070 1.0000
5.500 0.9361 0.01853 0.00944 -0.0542 0.4943 1.0000
5.750 0.9617 0.01896 0.00998 -0.0539 0.4819 1.0000
6.000 0.9873 0.01945 0.01053 -0.0536 0.4701 1.0000
6.250 1.0130 0.01998 0.01111 -0.0533 0.4589 1.0000
6.500 1.0388 0.02052 0.01169 -0.0530 0.4477 1.0000
6.750 1.0645 0.02107 0.01231 -0.0527 0.4356 1.0000
7.000 1.0884 0.02156 0.01289 -0.0521 0.4202 1.0000
7.250 1.1110 0.02197 0.01342 -0.0512 0.4022 1.0000
7.500 1.1338 0.02233 0.01388 -0.0504 0.3841 1.0000
7.750 1.1569 0.02272 0.01434 -0.0496 0.3675 1.0000
8.000 1.1798 0.02314 0.01484 -0.0489 0.3516 1.0000
8.250 1.2011 0.02354 0.01543 -0.0479 0.3345 1.0000
8.500 1.2213 0.02388 0.01601 -0.0468 0.3158 1.0000
8.750 1.2412 0.02419 0.01650 -0.0455 0.2963 1.0000
9.000 1.2579 0.02447 0.01705 -0.0439 0.2703 1.0000
9.250 1.2693 0.02487 0.01753 -0.0415 0.2279 1.0000
9.500 1.2721 0.02643 0.01872 -0.0386 0.1728 1.0000
9.750 1.2749 0.02848 0.02052 -0.0359 0.1341 1.0000
10.000 1.2784 0.03043 0.02237 -0.0333 0.1093 1.0000
10.250 1.2774 0.03268 0.02455 -0.0303 0.0914 1.0000
10.500 1.2701 0.03518 0.02700 -0.0266 0.0778 1.0000
10.750 1.2645 0.03811 0.02988 -0.0233 0.0668 1.0000
11.000 1.2660 0.04114 0.03283 -0.0209 0.0578 1.0000
11.250 1.2687 0.04358 0.03541 -0.0190 0.0511 1.0000
11.500 1.2828 0.04675 0.03862 -0.0174 0.0459 1.0000
11.750 1.2939 0.04966 0.04181 -0.0158 0.0428 1.0000
12.000 1.3015 0.05267 0.04502 -0.0144 0.0404 1.0000
12.250 1.3175 0.05778 0.05015 -0.0140 0.0372 1.0000
12.500 1.3062 0.06050 0.05322 -0.0120 0.0366 1.0000
12.750 1.2954 0.06393 0.05700 -0.0109 0.0360 1.0000
13.000 1.2833 0.06791 0.06130 -0.0104 0.0356 1.0000
13.250 1.2695 0.07240 0.06608 -0.0104 0.0354 1.0000
13.500 1.2537 0.07733 0.07130 -0.0111 0.0354 1.0000
13.750 1.2362 0.08269 0.07692 -0.0125 0.0354 1.0000
14.000 1.2174 0.08849 0.08295 -0.0145 0.0356 1.0000
14.250 1.1977 0.09474 0.08941 -0.0172 0.0358 1.0000
14.500 1.1775 0.10145 0.09632 -0.0206 0.0360 1.0000
14.750 1.1570 0.10863 0.10367 -0.0245 0.0363 1.0000
15.000 1.1366 0.11633 0.11152 -0.0289 0.0366 1.0000
15.250 1.1173 0.12450 0.11980 -0.0337 0.0370 1.0000
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Polar data table (+)
Polar graphs
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