GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.07 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe188-il-1000000.txt Download as CSV file: xf-goe188-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2959 0.08422 0.08279 -0.0203 1.0000 0.0058
-8.250 -0.2944 0.08062 0.07920 -0.0212 1.0000 0.0059
-8.000 -0.3966 0.09046 0.08896 -0.0156 1.0000 0.0056
-7.750 -0.3932 0.08713 0.08565 -0.0171 1.0000 0.0056
-7.500 -0.3910 0.08383 0.08238 -0.0189 1.0000 0.0057
-7.250 -0.3841 0.08007 0.07863 -0.0225 1.0000 0.0057
-7.000 -0.3759 0.07627 0.07482 -0.0259 1.0000 0.0057
-6.750 -0.3628 0.07217 0.07072 -0.0302 0.9972 0.0058
-6.500 -0.3310 0.06666 0.06514 -0.0393 0.9608 0.0059
-6.250 -0.3107 0.06249 0.06066 -0.0437 0.8760 0.0060
-6.000 -0.2941 0.05878 0.05675 -0.0465 0.8434 0.0061
-5.750 -0.2748 0.05501 0.05282 -0.0492 0.8240 0.0062
-5.500 -0.2540 0.05131 0.04896 -0.0516 0.8090 0.0064
-5.250 -0.2320 0.04770 0.04520 -0.0536 0.7961 0.0066
-5.000 -0.2088 0.04422 0.04155 -0.0552 0.7840 0.0068
-4.750 -0.1846 0.04087 0.03802 -0.0564 0.7726 0.0072
-4.500 -0.1574 0.03764 0.03459 -0.0570 0.7617 0.0078
-4.250 -0.1272 0.03474 0.03144 -0.0570 0.7520 0.0081
-4.000 -0.1007 0.03196 0.02844 -0.0570 0.7426 0.0081
-3.750 -0.0743 0.02916 0.02539 -0.0568 0.7332 0.0082
-3.500 -0.0511 0.02451 0.02042 -0.0570 0.7249 0.0086
-3.250 -0.0263 0.02293 0.01868 -0.0573 0.7155 0.0090
-3.000 0.0004 0.02137 0.01695 -0.0573 0.7057 0.0097
-2.750 0.0294 0.01998 0.01533 -0.0568 0.6968 0.0111
-2.500 0.0595 0.01959 0.01469 -0.0561 0.6883 0.0118
-2.250 0.0878 0.01831 0.01316 -0.0558 0.6799 0.0118
-2.000 0.1151 0.01516 0.00968 -0.0557 0.6725 0.0124
-1.750 0.1427 0.01396 0.00839 -0.0558 0.6640 0.0129
-1.500 0.1709 0.01308 0.00738 -0.0558 0.6559 0.0135
-1.250 0.1993 0.01234 0.00651 -0.0557 0.6476 0.0146
-1.000 0.2282 0.01193 0.00599 -0.0556 0.6399 0.0163
-0.750 0.2572 0.01204 0.00596 -0.0554 0.6319 0.0172
-0.250 0.3135 0.00956 0.00332 -0.0550 0.6159 0.0179
0.000 0.3415 0.00899 0.00272 -0.0550 0.6064 0.0181
0.250 0.3701 0.00889 0.00259 -0.0550 0.5967 0.0171
0.500 0.3983 0.00832 0.00195 -0.0550 0.5868 0.0166
0.750 0.4267 0.00810 0.00164 -0.0551 0.5742 0.0178
1.000 0.4552 0.00794 0.00139 -0.0551 0.5583 0.0203
1.250 0.4834 0.00792 0.00128 -0.0552 0.5376 0.0238
1.500 0.5114 0.00797 0.00122 -0.0553 0.5098 0.0358
1.750 0.5347 0.00579 0.00133 -0.0550 0.4796 1.0000
2.000 0.5619 0.00601 0.00137 -0.0550 0.4512 1.0000
2.250 0.5892 0.00620 0.00144 -0.0550 0.4291 1.0000
2.500 0.6168 0.00638 0.00152 -0.0550 0.4117 1.0000
2.750 0.6444 0.00654 0.00159 -0.0551 0.3980 1.0000
3.000 0.6722 0.00669 0.00168 -0.0552 0.3870 1.0000
3.250 0.6999 0.00684 0.00177 -0.0553 0.3772 1.0000
3.500 0.7277 0.00697 0.00187 -0.0554 0.3682 1.0000
3.750 0.7555 0.00710 0.00197 -0.0555 0.3600 1.0000
4.000 0.7832 0.00726 0.00208 -0.0556 0.3518 1.0000
4.250 0.8111 0.00737 0.00219 -0.0557 0.3451 1.0000
4.500 0.8386 0.00754 0.00233 -0.0558 0.3363 1.0000
4.750 0.8662 0.00768 0.00245 -0.0559 0.3266 1.0000
5.000 0.8938 0.00783 0.00258 -0.0560 0.3172 1.0000
5.250 0.9211 0.00802 0.00273 -0.0561 0.3085 1.0000
5.500 0.9487 0.00815 0.00288 -0.0562 0.3002 1.0000
5.750 0.9760 0.00832 0.00304 -0.0563 0.2915 1.0000
6.000 1.0032 0.00850 0.00321 -0.0564 0.2824 1.0000
6.250 1.0304 0.00867 0.00338 -0.0565 0.2723 1.0000
6.500 1.0573 0.00888 0.00358 -0.0565 0.2590 1.0000
6.750 1.0837 0.00914 0.00380 -0.0565 0.2430 1.0000
7.000 1.1092 0.00952 0.00407 -0.0564 0.2163 1.0000
7.250 1.1331 0.01008 0.00446 -0.0561 0.1820 1.0000
7.500 1.1569 0.01066 0.00490 -0.0558 0.1531 1.0000
7.750 1.1794 0.01139 0.00541 -0.0553 0.1135 1.0000
8.000 1.1993 0.01241 0.00616 -0.0545 0.0681 1.0000
8.250 1.2228 0.01296 0.00667 -0.0541 0.0549 1.0000
8.500 1.2465 0.01345 0.00715 -0.0537 0.0463 1.0000
8.750 1.2699 0.01396 0.00763 -0.0533 0.0386 1.0000
9.000 1.2934 0.01443 0.00810 -0.0529 0.0310 1.0000
9.250 1.3123 0.01541 0.00893 -0.0519 0.0126 1.0000
9.500 1.3325 0.01624 0.00980 -0.0510 0.0090 1.0000
9.750 1.3538 0.01685 0.01051 -0.0502 0.0079 1.0000
10.000 1.3731 0.01766 0.01139 -0.0492 0.0068 1.0000
10.250 1.3882 0.01884 0.01272 -0.0476 0.0060 1.0000
10.500 1.4073 0.01954 0.01349 -0.0466 0.0057 1.0000
10.750 1.4243 0.02038 0.01443 -0.0453 0.0053 1.0000
11.000 1.4394 0.02131 0.01545 -0.0438 0.0050 1.0000
11.250 1.4527 0.02229 0.01652 -0.0421 0.0047 1.0000
11.500 1.4628 0.02336 0.01770 -0.0400 0.0044 1.0000
11.750 1.4655 0.02462 0.01907 -0.0367 0.0042 1.0000
12.000 1.4628 0.02642 0.02100 -0.0334 0.0040 1.0000
12.250 1.4491 0.02943 0.02420 -0.0302 0.0038 1.0000
12.500 1.4451 0.03211 0.02703 -0.0287 0.0037 1.0000
12.750 1.4550 0.03363 0.02864 -0.0283 0.0036 1.0000
13.000 1.4585 0.03591 0.03103 -0.0279 0.0034 1.0000
13.250 1.4595 0.03855 0.03378 -0.0277 0.0033 1.0000
13.500 1.4574 0.04168 0.03704 -0.0277 0.0032 1.0000
13.750 1.4539 0.04506 0.04055 -0.0278 0.0031 1.0000
14.000 1.4483 0.04885 0.04446 -0.0283 0.0031 1.0000
14.250 1.4420 0.05279 0.04853 -0.0288 0.0030 1.0000
14.500 1.4342 0.05702 0.05289 -0.0296 0.0029 1.0000
14.750 1.4254 0.06150 0.05749 -0.0307 0.0029 1.0000
15.000 1.4151 0.06630 0.06242 -0.0319 0.0029 1.0000
15.250 1.4047 0.07137 0.06761 -0.0334 0.0028 1.0000
15.500 1.3944 0.07661 0.07297 -0.0351 0.0028 1.0000
15.750 1.3838 0.08203 0.07852 -0.0370 0.0028 1.0000
16.000 1.3722 0.08775 0.08435 -0.0391 0.0027 1.0000
16.250 1.3598 0.09365 0.09038 -0.0413 0.0027 1.0000
16.500 1.3479 0.09956 0.09640 -0.0436 0.0027 1.0000
16.750 1.3363 0.10555 0.10250 -0.0461 0.0027 1.0000
17.000 1.3237 0.11180 0.10887 -0.0487 0.0027 1.0000
17.250 1.3118 0.11798 0.11516 -0.0513 0.0026 1.0000
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