GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 1,000,000 Max Cl/Cd: 139 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe195-il-1000000.txt Download as CSV file: xf-goe195-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3619 0.09159 0.08997 -0.0321 1.0000 0.0185
-8.500 -0.3445 0.08932 0.08770 -0.0343 0.9988 0.0188
-8.250 -0.3268 0.08674 0.08511 -0.0371 0.9972 0.0192
-8.000 -0.3095 0.08350 0.08188 -0.0411 0.9952 0.0197
-7.750 -0.2932 0.07980 0.07817 -0.0457 0.9922 0.0205
-7.500 -0.2691 0.07096 0.06932 -0.0600 0.9866 0.0223
-7.250 -0.2457 0.05862 0.05694 -0.0781 0.9823 0.0227
-7.000 -0.2234 0.05616 0.05447 -0.0819 0.9769 0.0231
-6.750 -0.1965 0.05348 0.05177 -0.0868 0.9726 0.0235
-6.500 -0.1698 0.04980 0.04806 -0.0928 0.9661 0.0240
-6.250 -0.1377 0.04373 0.04191 -0.1027 0.9588 0.0253
-6.000 -0.0841 0.02093 0.01768 -0.1314 0.9486 0.0286
-5.750 -0.0578 0.01975 0.01646 -0.1318 0.9427 0.0291
-5.500 -0.0316 0.01859 0.01519 -0.1321 0.9347 0.0298
-5.250 -0.0046 0.01747 0.01391 -0.1324 0.9273 0.0307
-5.000 0.0229 0.01638 0.01263 -0.1326 0.9184 0.0318
-4.750 0.0508 0.01583 0.01188 -0.1326 0.9093 0.0331
-4.500 0.0786 0.01448 0.01029 -0.1327 0.8986 0.0331
-4.250 0.1070 0.01162 0.00699 -0.1331 0.8872 0.0296
-4.000 0.1349 0.01074 0.00591 -0.1329 0.8744 0.0289
-3.750 0.1626 0.01016 0.00520 -0.1327 0.8596 0.0289
-3.500 0.1901 0.00965 0.00459 -0.1325 0.8432 0.0290
-3.250 0.2177 0.00925 0.00408 -0.1323 0.8254 0.0294
-3.000 0.2451 0.00897 0.00371 -0.1320 0.8067 0.0301
-2.750 0.2727 0.00868 0.00332 -0.1318 0.7886 0.0305
-2.500 0.3005 0.00844 0.00299 -0.1317 0.7721 0.0309
-2.250 0.3284 0.00824 0.00270 -0.1315 0.7578 0.0314
-1.750 0.3845 0.00792 0.00223 -0.1313 0.7317 0.0322
-1.500 0.4127 0.00779 0.00203 -0.1312 0.7193 0.0326
-1.250 0.4408 0.00769 0.00187 -0.1311 0.7065 0.0330
-1.000 0.4689 0.00762 0.00173 -0.1310 0.6922 0.0335
-0.750 0.4968 0.00758 0.00163 -0.1308 0.6746 0.0341
-0.500 0.5244 0.00750 0.00141 -0.1306 0.6483 0.0357
0.000 0.5776 0.00773 0.00128 -0.1299 0.5682 0.0394
0.250 0.6050 0.00782 0.00127 -0.1297 0.5506 0.0416
0.500 0.6330 0.00755 0.00126 -0.1298 0.5403 0.1584
0.750 0.6609 0.00745 0.00138 -0.1298 0.5322 0.2491
1.000 0.6886 0.00752 0.00146 -0.1297 0.5241 0.2717
1.250 0.7164 0.00759 0.00152 -0.1296 0.5162 0.2858
1.500 0.7441 0.00766 0.00160 -0.1295 0.5093 0.2974
1.750 0.7721 0.00769 0.00166 -0.1294 0.5026 0.3099
2.000 0.7997 0.00777 0.00173 -0.1292 0.4962 0.3206
2.250 0.8278 0.00778 0.00180 -0.1292 0.4911 0.3366
2.500 0.8556 0.00777 0.00188 -0.1291 0.4845 0.3683
2.750 0.8832 0.00763 0.00204 -0.1292 0.4756 0.5057
3.000 0.9106 0.00755 0.00218 -0.1291 0.4657 0.6150
3.250 0.9343 0.00689 0.00227 -0.1281 0.4586 1.0000
3.500 0.9617 0.00702 0.00235 -0.1279 0.4486 1.0000
3.750 0.9892 0.00714 0.00243 -0.1277 0.4349 1.0000
4.000 1.0161 0.00731 0.00253 -0.1275 0.4172 1.0000
4.250 1.0428 0.00751 0.00264 -0.1272 0.3937 1.0000
4.500 1.0684 0.00783 0.00281 -0.1268 0.3617 1.0000
4.750 1.0929 0.00827 0.00306 -0.1262 0.3224 1.0000
5.000 1.1162 0.00886 0.00338 -0.1255 0.2733 1.0000
5.250 1.1402 0.00937 0.00370 -0.1248 0.2379 1.0000
5.500 1.1644 0.00983 0.00401 -0.1242 0.2077 1.0000
5.750 1.1878 0.01038 0.00436 -0.1235 0.1692 1.0000
6.000 1.2092 0.01116 0.00484 -0.1226 0.1211 1.0000
6.250 1.2325 0.01169 0.00525 -0.1218 0.0990 1.0000
6.500 1.2560 0.01218 0.00563 -0.1211 0.0791 1.0000
6.750 1.2758 0.01308 0.00625 -0.1198 0.0396 1.0000
7.000 1.2990 0.01357 0.00672 -0.1190 0.0334 1.0000
7.250 1.3230 0.01394 0.00712 -0.1183 0.0316 1.0000
7.500 1.3460 0.01441 0.00761 -0.1175 0.0294 1.0000
7.750 1.3674 0.01504 0.00828 -0.1164 0.0268 1.0000
8.000 1.3912 0.01538 0.00864 -0.1157 0.0259 1.0000
8.250 1.4141 0.01578 0.00907 -0.1149 0.0246 1.0000
8.500 1.4361 0.01626 0.00958 -0.1140 0.0232 1.0000
8.750 1.4550 0.01702 0.01038 -0.1125 0.0215 1.0000
9.000 1.4760 0.01753 0.01094 -0.1114 0.0207 1.0000
9.250 1.4977 0.01794 0.01139 -0.1105 0.0198 1.0000
9.500 1.5188 0.01839 0.01186 -0.1094 0.0188 1.0000
9.750 1.5386 0.01891 0.01239 -0.1082 0.0178 1.0000
10.000 1.5512 0.02000 0.01355 -0.1058 0.0166 1.0000
10.250 1.5711 0.02043 0.01402 -0.1046 0.0162 1.0000
10.500 1.5890 0.02096 0.01461 -0.1031 0.0156 1.0000
10.750 1.6044 0.02154 0.01524 -0.1012 0.0150 1.0000
11.000 1.6183 0.02216 0.01589 -0.0990 0.0145 1.0000
11.250 1.6309 0.02287 0.01663 -0.0967 0.0139 1.0000
11.500 1.6374 0.02399 0.01781 -0.0937 0.0133 1.0000
11.750 1.6426 0.02524 0.01915 -0.0907 0.0129 1.0000
12.000 1.6554 0.02601 0.01999 -0.0888 0.0125 1.0000
12.250 1.6657 0.02699 0.02104 -0.0867 0.0122 1.0000
12.500 1.6748 0.02810 0.02223 -0.0846 0.0118 1.0000
12.750 1.6833 0.02930 0.02349 -0.0827 0.0115 1.0000
13.000 1.6912 0.03059 0.02485 -0.0808 0.0112 1.0000
13.250 1.6979 0.03205 0.02637 -0.0790 0.0109 1.0000
13.500 1.7015 0.03385 0.02825 -0.0771 0.0106 1.0000
13.750 1.6994 0.03629 0.03078 -0.0752 0.0103 1.0000
14.000 1.6886 0.03976 0.03440 -0.0732 0.0101 1.0000
14.250 1.6891 0.04227 0.03702 -0.0721 0.0099 1.0000
14.500 1.6917 0.04466 0.03951 -0.0713 0.0098 1.0000
14.750 1.6928 0.04728 0.04223 -0.0706 0.0097 1.0000
15.000 1.6917 0.05023 0.04529 -0.0701 0.0095 1.0000
15.250 1.6902 0.05333 0.04850 -0.0698 0.0094 1.0000
15.500 1.6874 0.05669 0.05197 -0.0696 0.0092 1.0000
15.750 1.6839 0.06027 0.05565 -0.0698 0.0090 1.0000
16.000 1.6799 0.06407 0.05955 -0.0701 0.0089 1.0000
16.250 1.6758 0.06801 0.06360 -0.0707 0.0087 1.0000
16.500 1.6703 0.07220 0.06790 -0.0715 0.0086 1.0000
16.750 1.6633 0.07672 0.07252 -0.0724 0.0085 1.0000
17.000 1.6555 0.08141 0.07731 -0.0735 0.0084 1.0000
17.250 1.6465 0.08634 0.08234 -0.0748 0.0083 1.0000
17.500 1.6353 0.09164 0.08775 -0.0762 0.0082 1.0000
17.750 1.6231 0.09723 0.09345 -0.0779 0.0081 1.0000
18.000 1.6101 0.10304 0.09936 -0.0798 0.0081 1.0000
18.250 1.5967 0.10900 0.10543 -0.0818 0.0080 1.0000
18.500 1.5819 0.11531 0.11185 -0.0842 0.0079 1.0000
18.750 1.5673 0.12172 0.11838 -0.0868 0.0078 1.0000
19.000 1.5520 0.12838 0.12515 -0.0897 0.0077 1.0000
19.250 1.5368 0.13513 0.13202 -0.0928 0.0077 1.0000
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