GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 500,000 Max Cl/Cd: 83.53 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe650-il-500000-n5.txt Download as CSV file: xf-goe650-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7603 0.08785 0.08424 -0.0689 1.0000 0.0262
-15.750 -0.7716 0.08300 0.07933 -0.0712 1.0000 0.0265
-15.500 -0.7830 0.07825 0.07451 -0.0734 1.0000 0.0268
-15.250 -0.7934 0.07388 0.07008 -0.0753 1.0000 0.0269
-15.000 -0.8065 0.06928 0.06541 -0.0773 1.0000 0.0271
-14.750 -0.8210 0.06481 0.06087 -0.0791 1.0000 0.0273
-14.500 -0.8369 0.06058 0.05658 -0.0804 1.0000 0.0274
-14.250 -0.8549 0.05641 0.05235 -0.0815 1.0000 0.0275
-14.000 -0.8774 0.05216 0.04803 -0.0822 1.0000 0.0276
-13.750 -0.8811 0.04711 0.04288 -0.0876 0.9978 0.0278
-13.500 -0.8794 0.04198 0.03762 -0.0944 0.9936 0.0280
-13.250 -0.8822 0.03673 0.03224 -0.1011 0.9866 0.0281
-13.000 -0.8729 0.03096 0.02631 -0.1106 0.9800 0.0284
-12.750 -0.8540 0.02703 0.02221 -0.1174 0.9742 0.0289
-12.500 -0.8288 0.02504 0.02012 -0.1208 0.9713 0.0293
-12.250 -0.8093 0.02372 0.01870 -0.1216 0.9658 0.0298
-12.000 -0.7851 0.02252 0.01741 -0.1229 0.9618 0.0303
-11.750 -0.7577 0.02145 0.01625 -0.1244 0.9593 0.0308
-11.500 -0.7280 0.02048 0.01518 -0.1261 0.9575 0.0313
-11.250 -0.7077 0.01974 0.01435 -0.1256 0.9510 0.0319
-11.000 -0.6792 0.01900 0.01351 -0.1266 0.9476 0.0324
-10.500 -0.6188 0.01725 0.01162 -0.1295 0.9421 0.0336
-10.250 -0.5954 0.01661 0.01092 -0.1292 0.9356 0.0342
-10.000 -0.5653 0.01598 0.01022 -0.1302 0.9315 0.0350
-9.750 -0.5333 0.01539 0.00956 -0.1315 0.9282 0.0358
-9.500 -0.5068 0.01493 0.00902 -0.1315 0.9226 0.0367
-9.250 -0.4783 0.01449 0.00851 -0.1318 0.9172 0.0374
-9.000 -0.4484 0.01392 0.00788 -0.1326 0.9127 0.0387
-8.750 -0.4213 0.01347 0.00738 -0.1326 0.9070 0.0400
-8.500 -0.3942 0.01309 0.00694 -0.1326 0.9008 0.0415
-8.250 -0.3648 0.01270 0.00649 -0.1330 0.8955 0.0435
-8.000 -0.3389 0.01231 0.00607 -0.1327 0.8890 0.0468
-7.750 -0.3125 0.01193 0.00568 -0.1325 0.8821 0.0524
-7.500 -0.2845 0.01154 0.00530 -0.1326 0.8763 0.0634
-7.250 -0.2594 0.01125 0.00503 -0.1321 0.8689 0.0734
-7.000 -0.2316 0.01103 0.00478 -0.1320 0.8618 0.0813
-6.750 -0.2049 0.01083 0.00456 -0.1317 0.8545 0.0875
-6.500 -0.1779 0.01066 0.00435 -0.1313 0.8468 0.0923
-6.250 -0.1504 0.01050 0.00416 -0.1311 0.8401 0.0974
-6.000 -0.1237 0.01038 0.00399 -0.1307 0.8322 0.1014
-5.750 -0.0963 0.01023 0.00380 -0.1305 0.8254 0.1059
-5.500 -0.0696 0.01010 0.00366 -0.1301 0.8187 0.1109
-5.250 -0.0425 0.01000 0.00351 -0.1297 0.8115 0.1156
-5.000 -0.0156 0.00987 0.00336 -0.1294 0.8046 0.1201
-4.750 0.0112 0.00977 0.00324 -0.1290 0.7971 0.1246
-4.500 0.0387 0.00971 0.00310 -0.1287 0.7910 0.1279
-4.250 0.0655 0.00958 0.00298 -0.1283 0.7854 0.1326
-4.000 0.0925 0.00949 0.00288 -0.1279 0.7795 0.1384
-3.750 0.1200 0.00944 0.00278 -0.1276 0.7739 0.1431
-3.500 0.1469 0.00932 0.00268 -0.1273 0.7687 0.1491
-3.250 0.1740 0.00925 0.00260 -0.1269 0.7634 0.1549
-3.000 0.2014 0.00919 0.00251 -0.1266 0.7584 0.1596
-2.750 0.2285 0.00911 0.00243 -0.1263 0.7532 0.1657
-2.500 0.2552 0.00905 0.00237 -0.1258 0.7463 0.1722
-2.250 0.2818 0.00900 0.00229 -0.1253 0.7383 0.1792
-2.000 0.3082 0.00894 0.00224 -0.1248 0.7304 0.1872
-1.750 0.3347 0.00889 0.00219 -0.1243 0.7224 0.1956
-1.500 0.3611 0.00885 0.00215 -0.1238 0.7145 0.2061
-1.250 0.3870 0.00880 0.00212 -0.1232 0.7048 0.2192
-1.000 0.4129 0.00876 0.00210 -0.1226 0.6953 0.2336
-0.750 0.4386 0.00874 0.00208 -0.1219 0.6851 0.2476
-0.500 0.4648 0.00871 0.00208 -0.1213 0.6757 0.2631
-0.250 0.4903 0.00870 0.00209 -0.1206 0.6652 0.2793
0.000 0.5159 0.00870 0.00210 -0.1199 0.6532 0.2939
0.250 0.5411 0.00871 0.00212 -0.1192 0.6396 0.3081
0.500 0.5656 0.00874 0.00214 -0.1183 0.6235 0.3219
0.750 0.5889 0.00882 0.00217 -0.1171 0.6021 0.3344
1.000 0.6114 0.00894 0.00221 -0.1158 0.5797 0.3460
1.250 0.6335 0.00908 0.00229 -0.1144 0.5573 0.3578
1.500 0.6556 0.00925 0.00238 -0.1131 0.5369 0.3695
1.750 0.6783 0.00940 0.00249 -0.1118 0.5197 0.3806
2.000 0.7011 0.00955 0.00260 -0.1107 0.5040 0.3914
2.250 0.7240 0.00971 0.00272 -0.1095 0.4886 0.4032
2.500 0.7468 0.00985 0.00284 -0.1083 0.4736 0.4144
2.750 0.7692 0.01001 0.00297 -0.1071 0.4560 0.4247
3.000 0.7908 0.01020 0.00311 -0.1057 0.4349 0.4376
3.250 0.8106 0.01043 0.00327 -0.1040 0.4087 0.4531
3.500 0.8289 0.01071 0.00347 -0.1021 0.3779 0.4707
3.750 0.8467 0.01102 0.00369 -0.1000 0.3503 0.4872
4.000 0.8651 0.01130 0.00390 -0.0981 0.3295 0.5025
4.250 0.8838 0.01152 0.00410 -0.0962 0.3143 0.5190
4.500 0.9024 0.01173 0.00431 -0.0943 0.3016 0.5378
4.750 0.9209 0.01194 0.00453 -0.0924 0.2892 0.5612
5.000 0.9406 0.01210 0.00475 -0.0907 0.2796 0.5876
5.250 0.9588 0.01230 0.00500 -0.0888 0.2696 0.6221
5.500 0.9770 0.01240 0.00524 -0.0869 0.2601 0.6771
6.000 1.0566 0.01265 0.00595 -0.0924 0.2381 1.0000
6.250 1.0765 0.01292 0.00619 -0.0909 0.2295 1.0000
6.500 1.0947 0.01327 0.00647 -0.0890 0.2190 1.0000
6.750 1.1142 0.01356 0.00674 -0.0875 0.2104 1.0000
7.000 1.1328 0.01391 0.00705 -0.0858 0.2025 1.0000
7.250 1.1520 0.01423 0.00735 -0.0842 0.1947 1.0000
7.500 1.1701 0.01461 0.00769 -0.0825 0.1874 1.0000
7.750 1.1887 0.01497 0.00803 -0.0810 0.1787 1.0000
8.000 1.2062 0.01539 0.00841 -0.0792 0.1705 1.0000
8.250 1.2241 0.01580 0.00879 -0.0776 0.1628 1.0000
8.500 1.2415 0.01624 0.00922 -0.0759 0.1563 1.0000
8.750 1.2591 0.01668 0.00964 -0.0743 0.1498 1.0000
9.000 1.2758 0.01717 0.01011 -0.0727 0.1440 1.0000
9.250 1.2934 0.01762 0.01057 -0.0711 0.1389 1.0000
9.500 1.3096 0.01816 0.01110 -0.0695 0.1330 1.0000
9.750 1.3257 0.01871 0.01164 -0.0678 0.1272 1.0000
10.000 1.3417 0.01928 0.01221 -0.0662 0.1219 1.0000
10.250 1.3567 0.01992 0.01284 -0.0645 0.1172 1.0000
10.500 1.3731 0.02048 0.01343 -0.0631 0.1136 1.0000
10.750 1.3882 0.02113 0.01410 -0.0615 0.1094 1.0000
11.000 1.4022 0.02187 0.01483 -0.0599 0.1054 1.0000
11.250 1.4173 0.02255 0.01555 -0.0584 0.1008 1.0000
11.500 1.4301 0.02340 0.01638 -0.0568 0.0953 1.0000
11.750 1.4438 0.02420 0.01721 -0.0553 0.0913 1.0000
12.000 1.4568 0.02507 0.01809 -0.0538 0.0861 1.0000
12.250 1.4683 0.02605 0.01908 -0.0522 0.0809 1.0000
12.500 1.4786 0.02716 0.02017 -0.0506 0.0736 1.0000
12.750 1.4866 0.02845 0.02142 -0.0489 0.0629 1.0000
13.250 1.4889 0.03221 0.02503 -0.0449 0.0382 1.0000
13.500 1.4939 0.03388 0.02673 -0.0433 0.0350 1.0000
13.750 1.4995 0.03554 0.02844 -0.0419 0.0333 1.0000
14.000 1.5063 0.03715 0.03012 -0.0407 0.0321 1.0000
14.250 1.5126 0.03884 0.03188 -0.0395 0.0311 1.0000
14.500 1.5174 0.04070 0.03380 -0.0384 0.0302 1.0000
14.750 1.5211 0.04272 0.03590 -0.0374 0.0294 1.0000
15.000 1.5222 0.04508 0.03832 -0.0365 0.0284 1.0000
15.250 1.5256 0.04726 0.04059 -0.0357 0.0279 1.0000
15.500 1.5288 0.04950 0.04292 -0.0351 0.0274 1.0000
15.750 1.5308 0.05196 0.04547 -0.0345 0.0268 1.0000
16.000 1.5311 0.05466 0.04827 -0.0341 0.0263 1.0000
16.250 1.5299 0.05764 0.05134 -0.0339 0.0258 1.0000
16.500 1.5272 0.06087 0.05465 -0.0339 0.0253 1.0000
16.750 1.5224 0.06447 0.05835 -0.0340 0.0249 1.0000
17.000 1.5155 0.06848 0.06247 -0.0345 0.0245 1.0000
17.250 1.5061 0.07293 0.06702 -0.0352 0.0241 1.0000
17.500 1.5022 0.07669 0.07090 -0.0358 0.0238 1.0000
17.750 1.4959 0.08087 0.07519 -0.0366 0.0235 1.0000
18.000 1.4886 0.08527 0.07971 -0.0377 0.0232 1.0000
18.250 1.4792 0.09008 0.08464 -0.0390 0.0229 1.0000
18.500 1.4684 0.09515 0.08983 -0.0405 0.0227 1.0000
18.750 1.4571 0.10041 0.09521 -0.0422 0.0224 1.0000
19.000 1.4445 0.10601 0.10092 -0.0443 0.0221 1.0000
19.250 1.4321 0.11168 0.10671 -0.0464 0.0219 1.0000
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