GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 500,000 Max Cl/Cd: 116.71 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe195-il-500000.txt Download as CSV file: xf-goe195-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 195 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3318 0.09503 0.09274 -0.0316 1.0000 0.0267
-8.250 -0.3502 0.09271 0.09048 -0.0310 1.0000 0.0273
-8.000 -0.3668 0.09115 0.08898 -0.0282 1.0000 0.0274
-7.750 -0.3532 0.08597 0.08380 -0.0351 0.9966 0.0276
-7.500 -0.3371 0.07983 0.07766 -0.0407 0.9942 0.0281
-7.250 -0.3167 0.07716 0.07499 -0.0433 0.9914 0.0285
-7.000 -0.2926 0.07433 0.07214 -0.0472 0.9883 0.0293
-6.750 -0.2640 0.07029 0.06808 -0.0543 0.9854 0.0306
-6.500 -0.2136 0.05903 0.05672 -0.0780 0.9790 0.0339
-6.250 -0.1848 0.05089 0.04853 -0.0891 0.9749 0.0350
-6.000 -0.1520 0.04853 0.04614 -0.0936 0.9731 0.0358
-5.750 -0.0831 0.03015 0.02682 -0.1239 0.9693 0.0430
-5.500 -0.0564 0.02835 0.02509 -0.1250 0.9642 0.0441
-5.250 -0.0235 0.02662 0.02330 -0.1275 0.9607 0.0458
-5.000 0.0162 0.02358 0.01957 -0.1323 0.9575 0.0528
-4.750 0.0417 0.02163 0.01769 -0.1329 0.9504 0.0548
-4.500 0.0720 0.02054 0.01654 -0.1338 0.9445 0.0580
-4.000 0.1364 0.01487 0.00959 -0.1351 0.9303 0.0428
-3.750 0.1649 0.01363 0.00826 -0.1350 0.9225 0.0407
-3.500 0.1932 0.01254 0.00701 -0.1349 0.9138 0.0400
-3.250 0.2210 0.01186 0.00622 -0.1346 0.9034 0.0404
-3.000 0.2491 0.01115 0.00541 -0.1344 0.8929 0.0402
-2.750 0.2770 0.01056 0.00473 -0.1341 0.8814 0.0402
-2.500 0.3047 0.01010 0.00419 -0.1338 0.8682 0.0405
-2.250 0.3324 0.00971 0.00373 -0.1335 0.8543 0.0408
-2.000 0.3602 0.00940 0.00334 -0.1332 0.8393 0.0411
-1.750 0.3879 0.00915 0.00300 -0.1329 0.8233 0.0415
-1.500 0.4156 0.00896 0.00273 -0.1326 0.8073 0.0421
-1.250 0.4435 0.00869 0.00235 -0.1324 0.7912 0.0438
-1.000 0.4711 0.00856 0.00212 -0.1321 0.7751 0.0452
-0.750 0.4987 0.00849 0.00195 -0.1318 0.7591 0.0472
-0.500 0.5262 0.00847 0.00183 -0.1314 0.7433 0.0499
-0.250 0.5537 0.00845 0.00175 -0.1311 0.7271 0.0573
0.000 0.5812 0.00804 0.00178 -0.1312 0.7102 0.2208
0.250 0.6083 0.00810 0.00187 -0.1309 0.6903 0.2681
0.500 0.6349 0.00820 0.00191 -0.1304 0.6660 0.2906
0.750 0.6615 0.00829 0.00193 -0.1300 0.6374 0.3067
1.000 0.6881 0.00839 0.00195 -0.1296 0.6116 0.3200
1.250 0.7148 0.00850 0.00199 -0.1293 0.5930 0.3340
1.500 0.7417 0.00858 0.00207 -0.1290 0.5784 0.3554
1.750 0.7686 0.00864 0.00217 -0.1288 0.5651 0.3838
2.000 0.7954 0.00861 0.00234 -0.1286 0.5536 0.4789
2.250 0.8214 0.00842 0.00255 -0.1283 0.5434 0.6546
2.500 0.8449 0.00791 0.00260 -0.1271 0.5342 1.0000
2.750 0.8719 0.00812 0.00272 -0.1268 0.5260 1.0000
3.000 0.8994 0.00825 0.00283 -0.1266 0.5182 1.0000
3.250 0.9263 0.00846 0.00298 -0.1263 0.5095 1.0000
3.500 0.9533 0.00861 0.00310 -0.1261 0.4984 1.0000
3.750 0.9803 0.00875 0.00322 -0.1258 0.4876 1.0000
4.000 1.0070 0.00893 0.00337 -0.1255 0.4775 1.0000
4.250 1.0339 0.00906 0.00349 -0.1252 0.4662 1.0000
4.500 1.0608 0.00920 0.00362 -0.1249 0.4533 1.0000
4.750 1.0873 0.00935 0.00377 -0.1246 0.4381 1.0000
5.000 1.1134 0.00954 0.00391 -0.1242 0.4193 1.0000
5.250 1.1388 0.00980 0.00408 -0.1237 0.3902 1.0000
5.500 1.1626 0.01021 0.00432 -0.1230 0.3519 1.0000
5.750 1.1850 0.01080 0.00469 -0.1221 0.3073 1.0000
6.000 1.2071 0.01144 0.00511 -0.1212 0.2672 1.0000
6.250 1.2294 0.01207 0.00555 -0.1203 0.2303 1.0000
6.500 1.2510 0.01275 0.00602 -0.1194 0.1936 1.0000
6.750 1.2709 0.01362 0.00660 -0.1182 0.1411 1.0000
7.000 1.2907 0.01446 0.00723 -0.1170 0.1078 1.0000
7.250 1.3109 0.01524 0.00785 -0.1158 0.0794 1.0000
7.500 1.3283 0.01628 0.00861 -0.1142 0.0454 1.0000
7.750 1.3489 0.01696 0.00931 -0.1130 0.0394 1.0000
8.000 1.3684 0.01771 0.01008 -0.1116 0.0359 1.0000
8.250 1.3868 0.01854 0.01097 -0.1100 0.0332 1.0000
8.500 1.4063 0.01920 0.01170 -0.1087 0.0316 1.0000
8.750 1.4240 0.01997 0.01255 -0.1071 0.0299 1.0000
9.000 1.4384 0.02098 0.01360 -0.1050 0.0282 1.0000
9.250 1.4469 0.02238 0.01509 -0.1021 0.0266 1.0000
9.500 1.4632 0.02307 0.01586 -0.1003 0.0257 1.0000
9.750 1.4750 0.02391 0.01678 -0.0977 0.0247 1.0000
10.000 1.4853 0.02486 0.01780 -0.0951 0.0238 1.0000
10.250 1.4944 0.02591 0.01890 -0.0925 0.0229 1.0000
10.500 1.4998 0.02726 0.02031 -0.0895 0.0220 1.0000
10.750 1.4942 0.02964 0.02277 -0.0854 0.0211 1.0000
11.000 1.5077 0.03046 0.02369 -0.0838 0.0206 1.0000
11.250 1.5171 0.03167 0.02500 -0.0818 0.0200 1.0000
11.500 1.5246 0.03310 0.02653 -0.0798 0.0194 1.0000
11.750 1.5315 0.03464 0.02815 -0.0779 0.0188 1.0000
12.000 1.5377 0.03628 0.02987 -0.0761 0.0182 1.0000
12.250 1.5431 0.03804 0.03170 -0.0744 0.0178 1.0000
12.500 1.5465 0.04008 0.03380 -0.0727 0.0174 1.0000
12.750 1.5458 0.04271 0.03649 -0.0707 0.0169 1.0000
13.000 1.5470 0.04523 0.03913 -0.0690 0.0165 1.0000
13.250 1.5515 0.04731 0.04136 -0.0680 0.0161 1.0000
13.500 1.5547 0.04961 0.04380 -0.0671 0.0157 1.0000
13.750 1.5567 0.05212 0.04644 -0.0662 0.0153 1.0000
14.000 1.5578 0.05475 0.04919 -0.0655 0.0150 1.0000
14.250 1.5578 0.05759 0.05215 -0.0649 0.0147 1.0000
14.500 1.5569 0.06061 0.05529 -0.0645 0.0144 1.0000
14.750 1.5553 0.06375 0.05854 -0.0643 0.0142 1.0000
15.000 1.5532 0.06706 0.06195 -0.0643 0.0139 1.0000
15.250 1.5505 0.07053 0.06553 -0.0644 0.0137 1.0000
15.500 1.5471 0.07419 0.06929 -0.0647 0.0135 1.0000
15.750 1.5419 0.07811 0.07331 -0.0649 0.0133 1.0000
16.000 1.5328 0.08262 0.07795 -0.0648 0.0131 1.0000
16.250 1.5195 0.08801 0.08353 -0.0654 0.0130 1.0000
16.500 1.5093 0.09326 0.08897 -0.0673 0.0129 1.0000
16.750 1.4978 0.09883 0.09472 -0.0693 0.0128 1.0000
17.000 1.4853 0.10479 0.10086 -0.0717 0.0127 1.0000
17.250 1.4718 0.11111 0.10737 -0.0745 0.0127 1.0000
17.500 1.4574 0.11779 0.11423 -0.0778 0.0126 1.0000
17.750 1.4416 0.12499 0.12162 -0.0815 0.0126 1.0000
18.000 1.4253 0.13260 0.12940 -0.0858 0.0126 1.0000
18.250 1.4081 0.14082 0.13781 -0.0908 0.0125 1.0000
18.500 1.3897 0.14973 0.14690 -0.0965 0.0125 1.0000
18.750 1.3701 0.15937 0.15672 -0.1029 0.0126 1.0000
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