GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 50,000 Max Cl/Cd: 44.03 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe195-il-50000-n5.txt Download as CSV file: xf-goe195-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3237 0.10652 0.09954 -0.0293 1.0000 0.1347
-7.750 -0.3422 0.10661 0.09981 -0.0289 1.0000 0.1361
-7.500 -0.3453 0.10410 0.09742 -0.0286 1.0000 0.1371
-7.250 -0.3312 0.09968 0.09299 -0.0261 1.0000 0.1395
-7.000 -0.3298 0.09721 0.09059 -0.0248 1.0000 0.1414
-6.750 -0.3308 0.09499 0.08846 -0.0240 1.0000 0.1432
-6.500 -0.3327 0.09283 0.08638 -0.0235 1.0000 0.1446
-6.000 -0.3363 0.08341 0.07699 -0.0323 1.0000 0.0901
-5.750 -0.3319 0.08047 0.07409 -0.0323 1.0000 0.0879
-5.250 -0.3021 0.06898 0.06245 -0.0484 1.0000 0.0780
-5.000 -0.2914 0.06615 0.05962 -0.0485 1.0000 0.0770
-4.750 -0.2761 0.06272 0.05616 -0.0506 1.0000 0.0757
-4.500 -0.2347 0.05695 0.05017 -0.0600 0.9950 0.0736
-4.250 -0.1815 0.04967 0.04249 -0.0726 0.9893 0.0723
-4.000 -0.1244 0.04281 0.03501 -0.0851 0.9850 0.0738
-3.750 -0.0740 0.03773 0.02923 -0.0935 0.9798 0.0737
-3.500 -0.0249 0.03400 0.02477 -0.1000 0.9752 0.0738
-3.250 0.0183 0.03149 0.02167 -0.1042 0.9689 0.0745
-3.000 0.0619 0.02966 0.01931 -0.1079 0.9631 0.0761
-2.750 0.0997 0.02838 0.01767 -0.1103 0.9551 0.0793
-2.500 0.1408 0.02735 0.01652 -0.1133 0.9486 0.0832
-2.250 0.1761 0.02651 0.01548 -0.1149 0.9391 0.0862
-2.000 0.2188 0.02573 0.01443 -0.1176 0.9327 0.0903
-1.750 0.2534 0.02515 0.01374 -0.1190 0.9221 0.0956
-1.500 0.2931 0.02458 0.01309 -0.1212 0.9137 0.1073
-1.250 0.3326 0.02389 0.01266 -0.1236 0.9047 0.1456
-1.000 0.3679 0.02371 0.01274 -0.1249 0.8939 0.2518
-0.750 0.4050 0.02367 0.01280 -0.1266 0.8846 0.3397
-0.500 0.4374 0.02352 0.01277 -0.1273 0.8733 0.3944
-0.250 0.4677 0.02337 0.01275 -0.1274 0.8611 0.4410
0.000 0.4998 0.02314 0.01255 -0.1279 0.8496 0.4718
0.250 0.5339 0.02283 0.01227 -0.1286 0.8392 0.5036
0.500 0.5657 0.02248 0.01204 -0.1289 0.8277 0.5466
0.750 0.5939 0.02206 0.01188 -0.1286 0.8150 0.6192
1.000 0.6186 0.02133 0.01157 -0.1272 0.8019 1.0000
1.250 0.6511 0.02143 0.01143 -0.1277 0.7900 1.0000
1.500 0.6848 0.02147 0.01126 -0.1282 0.7796 1.0000
1.750 0.7146 0.02165 0.01130 -0.1282 0.7670 1.0000
2.000 0.7433 0.02188 0.01142 -0.1281 0.7544 1.0000
2.250 0.7726 0.02210 0.01153 -0.1280 0.7424 1.0000
2.500 0.8034 0.02224 0.01158 -0.1280 0.7316 1.0000
2.750 0.8315 0.02250 0.01180 -0.1277 0.7192 1.0000
3.000 0.8579 0.02283 0.01210 -0.1272 0.7060 1.0000
3.250 0.8846 0.02314 0.01239 -0.1266 0.6930 1.0000
3.500 0.9114 0.02342 0.01267 -0.1260 0.6799 1.0000
3.750 0.9382 0.02367 0.01291 -0.1254 0.6668 1.0000
4.000 0.9652 0.02391 0.01314 -0.1247 0.6539 1.0000
4.250 0.9898 0.02426 0.01357 -0.1239 0.6400 1.0000
4.500 1.0142 0.02464 0.01401 -0.1230 0.6264 1.0000
4.750 1.0389 0.02501 0.01445 -0.1222 0.6131 1.0000
5.000 1.0639 0.02537 0.01491 -0.1213 0.6000 1.0000
5.250 1.0893 0.02571 0.01533 -0.1205 0.5869 1.0000
5.500 1.1149 0.02605 0.01575 -0.1197 0.5736 1.0000
5.750 1.1397 0.02639 0.01615 -0.1186 0.5582 1.0000
6.000 1.1632 0.02672 0.01656 -0.1173 0.5396 1.0000
6.250 1.1864 0.02700 0.01685 -0.1157 0.5187 1.0000
6.500 1.2073 0.02742 0.01732 -0.1141 0.4968 1.0000
6.750 1.2263 0.02797 0.01803 -0.1123 0.4751 1.0000
7.000 1.2461 0.02851 0.01871 -0.1107 0.4551 1.0000
7.250 1.2643 0.02910 0.01947 -0.1089 0.4340 1.0000
7.500 1.2806 0.02969 0.02023 -0.1068 0.4098 1.0000
7.750 1.2946 0.03026 0.02088 -0.1044 0.3808 1.0000
8.000 1.3063 0.03090 0.02149 -0.1017 0.3483 1.0000
8.250 1.3160 0.03182 0.02228 -0.0988 0.3149 1.0000
8.500 1.3248 0.03298 0.02335 -0.0961 0.2843 1.0000
8.750 1.3313 0.03438 0.02465 -0.0933 0.2549 1.0000
9.000 1.3344 0.03599 0.02617 -0.0903 0.2260 1.0000
9.250 1.3356 0.03773 0.02788 -0.0873 0.1992 1.0000
9.500 1.3363 0.03969 0.02985 -0.0845 0.1750 1.0000
9.750 1.3352 0.04191 0.03203 -0.0819 0.1540 1.0000
10.000 1.3322 0.04446 0.03449 -0.0795 0.1368 1.0000
10.250 1.3282 0.04727 0.03726 -0.0773 0.1217 1.0000
10.500 1.3233 0.05032 0.04024 -0.0754 0.1097 1.0000
10.750 1.3210 0.05331 0.04331 -0.0738 0.0988 1.0000
11.000 1.3203 0.05626 0.04635 -0.0722 0.0906 1.0000
11.250 1.3192 0.05927 0.04938 -0.0710 0.0843 1.0000
11.500 1.3212 0.06212 0.05240 -0.0698 0.0780 1.0000
11.750 1.3221 0.06506 0.05548 -0.0688 0.0730 1.0000
12.000 1.3246 0.06790 0.05837 -0.0677 0.0694 1.0000
12.250 1.3290 0.07075 0.06152 -0.0666 0.0653 1.0000
12.500 1.3300 0.07385 0.06474 -0.0660 0.0620 1.0000
12.750 1.3312 0.07686 0.06774 -0.0655 0.0594 1.0000
13.000 1.3333 0.08033 0.07158 -0.0648 0.0569 1.0000
13.250 1.3332 0.08406 0.07558 -0.0644 0.0549 1.0000
13.500 1.3302 0.08807 0.07980 -0.0645 0.0532 1.0000
13.750 1.3267 0.09206 0.08393 -0.0649 0.0516 1.0000
14.000 1.3270 0.09540 0.08730 -0.0650 0.0500 1.0000
14.250 1.3152 0.10117 0.09337 -0.0666 0.0492 1.0000
14.500 1.3002 0.10773 0.10025 -0.0692 0.0487 1.0000
14.750 1.2830 0.11505 0.10785 -0.0726 0.0484 1.0000
15.000 1.2636 0.12328 0.11631 -0.0770 0.0483 1.0000
15.250 1.2419 0.13268 0.12594 -0.0825 0.0485 1.0000
15.500 1.2183 0.14350 0.13695 -0.0894 0.0488 1.0000
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Polar data table (+)
Polar graphs
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