GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 500,000 Max Cl/Cd: 107.98 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe450-il-500000-n5.txt Download as CSV file: xf-goe450-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2363 0.08618 0.08379 -0.0629 0.9694 0.0128
-8.500 -0.2330 0.08046 0.07807 -0.0676 0.9608 0.0136
-8.250 -0.2296 0.07595 0.07356 -0.0711 0.9505 0.0139
-8.000 -0.2190 0.07373 0.07133 -0.0729 0.9425 0.0141
-7.750 -0.2057 0.07101 0.06859 -0.0759 0.9352 0.0144
-7.500 -0.1919 0.06783 0.06539 -0.0797 0.9274 0.0147
-7.250 -0.1762 0.06415 0.06167 -0.0844 0.9198 0.0153
-7.000 -0.1582 0.05863 0.05609 -0.0920 0.9114 0.0164
-6.750 -0.1350 0.04905 0.04633 -0.1044 0.9033 0.0176
-6.500 -0.1122 0.04671 0.04394 -0.1072 0.8967 0.0179
-6.250 -0.0880 0.04378 0.04091 -0.1105 0.8903 0.0184
-6.000 -0.0618 0.03986 0.03684 -0.1146 0.8837 0.0194
-5.750 -0.0336 0.02355 0.01948 -0.1245 0.8761 0.0221
-5.500 -0.0080 0.02283 0.01866 -0.1248 0.8701 0.0225
-5.250 0.0178 0.02191 0.01762 -0.1252 0.8633 0.0230
-5.000 0.0437 0.01994 0.01535 -0.1256 0.8569 0.0235
-4.750 0.0699 0.01807 0.01316 -0.1259 0.8493 0.0241
-4.500 0.0966 0.01660 0.01138 -0.1261 0.8423 0.0248
-4.250 0.1237 0.01556 0.01008 -0.1261 0.8342 0.0256
-4.000 0.1509 0.01460 0.00887 -0.1261 0.8262 0.0261
-3.750 0.1782 0.01386 0.00793 -0.1260 0.8170 0.0264
-3.500 0.2055 0.01327 0.00715 -0.1259 0.8076 0.0267
-3.250 0.2328 0.01278 0.00649 -0.1258 0.7974 0.0269
-3.000 0.2601 0.01236 0.00593 -0.1256 0.7855 0.0271
-2.750 0.2870 0.01155 0.00496 -0.1255 0.7732 0.0276
-2.500 0.3139 0.01098 0.00430 -0.1254 0.7606 0.0283
-2.250 0.3409 0.01062 0.00385 -0.1252 0.7477 0.0286
-2.000 0.3679 0.01033 0.00346 -0.1250 0.7344 0.0290
-1.750 0.3949 0.01009 0.00314 -0.1248 0.7208 0.0294
-1.250 0.4491 0.00972 0.00264 -0.1245 0.6953 0.0304
-1.000 0.4764 0.00958 0.00245 -0.1244 0.6844 0.0309
-0.750 0.5036 0.00947 0.00229 -0.1242 0.6744 0.0315
-0.500 0.5310 0.00938 0.00215 -0.1241 0.6646 0.0320
-0.250 0.5584 0.00931 0.00204 -0.1240 0.6553 0.0325
0.250 0.6133 0.00925 0.00191 -0.1239 0.6379 0.0342
0.500 0.6406 0.00924 0.00185 -0.1238 0.6297 0.0349
0.750 0.6680 0.00922 0.00179 -0.1237 0.6200 0.0363
1.000 0.6951 0.00924 0.00178 -0.1235 0.6093 0.0384
1.250 0.7218 0.00929 0.00179 -0.1233 0.5967 0.0416
1.500 0.7485 0.00929 0.00184 -0.1231 0.5835 0.0789
1.750 0.7750 0.00913 0.00194 -0.1231 0.5693 0.2093
2.000 0.8014 0.00874 0.00214 -0.1232 0.5573 0.4733
2.250 0.8248 0.00773 0.00226 -0.1222 0.5462 1.0000
2.500 0.8509 0.00790 0.00234 -0.1219 0.5293 1.0000
2.750 0.8763 0.00812 0.00244 -0.1215 0.5084 1.0000
3.000 0.9016 0.00835 0.00256 -0.1210 0.4843 1.0000
3.250 0.9267 0.00860 0.00270 -0.1206 0.4640 1.0000
3.500 0.9520 0.00884 0.00285 -0.1202 0.4463 1.0000
3.750 0.9773 0.00909 0.00302 -0.1198 0.4285 1.0000
4.000 1.0023 0.00936 0.00321 -0.1193 0.4107 1.0000
4.250 1.0263 0.00970 0.00343 -0.1187 0.3874 1.0000
4.500 1.0508 0.01000 0.00365 -0.1182 0.3684 1.0000
4.750 1.0748 0.01033 0.00390 -0.1177 0.3468 1.0000
5.000 1.0981 0.01073 0.00417 -0.1170 0.3221 1.0000
5.250 1.1208 0.01117 0.00448 -0.1162 0.2944 1.0000
5.500 1.1425 0.01168 0.00482 -0.1153 0.2584 1.0000
5.750 1.1588 0.01266 0.00542 -0.1136 0.1877 1.0000
6.000 1.1791 0.01328 0.00589 -0.1125 0.1607 1.0000
6.250 1.2007 0.01376 0.00631 -0.1116 0.1430 1.0000
6.500 1.2162 0.01474 0.00697 -0.1098 0.0894 1.0000
6.750 1.2356 0.01535 0.00752 -0.1085 0.0720 1.0000
7.000 1.2540 0.01602 0.00808 -0.1071 0.0471 1.0000
7.250 1.2729 0.01661 0.00861 -0.1058 0.0383 1.0000
7.500 1.2924 0.01713 0.00914 -0.1045 0.0350 1.0000
7.750 1.3112 0.01767 0.00972 -0.1031 0.0321 1.0000
8.000 1.3298 0.01813 0.01023 -0.1017 0.0308 1.0000
8.250 1.3473 0.01861 0.01077 -0.1001 0.0294 1.0000
8.500 1.3637 0.01917 0.01138 -0.0983 0.0279 1.0000
8.750 1.3789 0.01981 0.01207 -0.0965 0.0263 1.0000
9.000 1.3918 0.02061 0.01293 -0.0943 0.0245 1.0000
9.250 1.4071 0.02125 0.01363 -0.0926 0.0234 1.0000
9.500 1.4230 0.02186 0.01431 -0.0910 0.0222 1.0000
9.750 1.4377 0.02255 0.01506 -0.0893 0.0208 1.0000
10.000 1.4515 0.02332 0.01587 -0.0876 0.0194 1.0000
10.250 1.4627 0.02428 0.01688 -0.0856 0.0180 1.0000
10.500 1.4760 0.02511 0.01778 -0.0839 0.0170 1.0000
10.750 1.4887 0.02601 0.01874 -0.0823 0.0159 1.0000
11.000 1.5003 0.02701 0.01979 -0.0806 0.0149 1.0000
11.250 1.5104 0.02814 0.02095 -0.0788 0.0140 1.0000
11.500 1.5186 0.02946 0.02235 -0.0769 0.0132 1.0000
11.750 1.5277 0.03075 0.02373 -0.0753 0.0125 1.0000
12.000 1.5361 0.03211 0.02518 -0.0737 0.0118 1.0000
12.250 1.5440 0.03357 0.02671 -0.0721 0.0112 1.0000
12.500 1.5504 0.03521 0.02840 -0.0706 0.0106 1.0000
12.750 1.5535 0.03719 0.03046 -0.0690 0.0101 1.0000
13.000 1.5576 0.03915 0.03253 -0.0676 0.0098 1.0000
13.250 1.5614 0.04121 0.03472 -0.0663 0.0094 1.0000
13.500 1.5641 0.04342 0.03704 -0.0652 0.0091 1.0000
13.750 1.5661 0.04578 0.03950 -0.0641 0.0088 1.0000
14.000 1.5676 0.04827 0.04211 -0.0632 0.0085 1.0000
14.250 1.5687 0.05089 0.04483 -0.0625 0.0083 1.0000
14.500 1.5689 0.05370 0.04773 -0.0619 0.0080 1.0000
14.750 1.5679 0.05672 0.05085 -0.0614 0.0078 1.0000
15.000 1.5649 0.06008 0.05431 -0.0611 0.0076 1.0000
15.250 1.5590 0.06390 0.05824 -0.0610 0.0074 1.0000
15.500 1.5553 0.06751 0.06198 -0.0610 0.0072 1.0000
15.750 1.5523 0.07110 0.06572 -0.0611 0.0071 1.0000
16.000 1.5486 0.07489 0.06963 -0.0614 0.0069 1.0000
16.250 1.5438 0.07889 0.07376 -0.0618 0.0068 1.0000
16.500 1.5387 0.08299 0.07799 -0.0624 0.0066 1.0000
16.750 1.5326 0.08734 0.08247 -0.0632 0.0065 1.0000
17.000 1.5262 0.09183 0.08708 -0.0641 0.0064 1.0000
17.250 1.5193 0.09648 0.09186 -0.0653 0.0063 1.0000
17.500 1.5116 0.10131 0.09681 -0.0666 0.0062 1.0000
17.750 1.5040 0.10620 0.10182 -0.0680 0.0061 1.0000
18.000 1.4956 0.11130 0.10705 -0.0697 0.0060 1.0000
18.250 1.4874 0.11648 0.11234 -0.0716 0.0059 1.0000
18.500 1.4788 0.12181 0.11779 -0.0736 0.0058 1.0000
18.750 1.4699 0.12723 0.12334 -0.0759 0.0058 1.0000
19.000 1.4609 0.13278 0.12900 -0.0783 0.0057 1.0000
19.250 1.4517 0.13847 0.13480 -0.0810 0.0056 1.0000
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