GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 200,000 Max Cl/Cd: 80.26 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe405-il-200000-n5.txt Download as CSV file: xf-goe405-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 405 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1456 0.11728 0.11368 -0.0717 0.9741 0.0212
-10.750 -0.1343 0.11339 0.10979 -0.0747 0.9706 0.0212
-10.500 -0.1205 0.10953 0.10592 -0.0777 0.9682 0.0207
-10.250 -0.1098 0.10600 0.10240 -0.0800 0.9635 0.0199
-10.000 -0.0981 0.10200 0.09839 -0.0832 0.9598 0.0193
-9.750 -0.0846 0.09770 0.09409 -0.0873 0.9572 0.0192
-9.500 -0.0754 0.09396 0.09034 -0.0900 0.9509 0.0189
-9.250 -0.0612 0.08969 0.08607 -0.0943 0.9473 0.0190
-9.000 -0.0495 0.08581 0.08219 -0.0980 0.9413 0.0197
-8.750 -0.0379 0.08122 0.07759 -0.1029 0.9356 0.0206
-8.500 -0.0319 0.07613 0.07250 -0.1075 0.9270 0.0213
-8.250 -0.0205 0.07112 0.06748 -0.1129 0.9204 0.0215
-8.000 -0.0200 0.06668 0.06303 -0.1161 0.9082 0.0217
-7.750 -0.0228 0.06147 0.05782 -0.1204 0.8954 0.0221
-7.500 -0.0106 0.05889 0.05521 -0.1232 0.8863 0.0227
-7.250 0.0063 0.05700 0.05328 -0.1255 0.8781 0.0236
-7.000 0.0175 0.05419 0.05040 -0.1281 0.8678 0.0250
-6.750 0.0260 0.04836 0.04445 -0.1335 0.8581 0.0259
-6.500 0.0042 0.02628 0.02105 -0.1455 0.8438 0.0278
-6.250 0.0208 0.02335 0.01749 -0.1452 0.8355 0.0294
-6.000 0.0467 0.02228 0.01630 -0.1456 0.8304 0.0313
-5.750 0.0680 0.02126 0.01506 -0.1448 0.8225 0.0329
-5.500 0.0938 0.02009 0.01355 -0.1449 0.8167 0.0350
-5.250 0.1180 0.01916 0.01230 -0.1444 0.8099 0.0370
-5.000 0.1438 0.01831 0.01115 -0.1441 0.8036 0.0382
-4.750 0.1690 0.01715 0.00980 -0.1439 0.7976 0.0403
-4.500 0.1941 0.01662 0.00916 -0.1435 0.7895 0.0424
-4.250 0.2206 0.01604 0.00840 -0.1432 0.7815 0.0441
-4.000 0.2468 0.01549 0.00768 -0.1427 0.7729 0.0456
-3.750 0.2727 0.01504 0.00707 -0.1423 0.7652 0.0473
-3.500 0.2993 0.01470 0.00658 -0.1420 0.7585 0.0493
-3.250 0.3254 0.01424 0.00606 -0.1417 0.7525 0.0520
-3.000 0.3511 0.01395 0.00570 -0.1412 0.7457 0.0546
-2.500 0.4038 0.01347 0.00505 -0.1405 0.7333 0.0633
-2.250 0.4305 0.01324 0.00479 -0.1402 0.7273 0.0739
-2.000 0.4564 0.01306 0.00467 -0.1399 0.7212 0.0964
-1.750 0.4823 0.01299 0.00461 -0.1395 0.7146 0.1197
-1.500 0.5097 0.01297 0.00453 -0.1394 0.7089 0.1361
-1.250 0.5348 0.01297 0.00449 -0.1388 0.7019 0.1481
-1.000 0.5616 0.01298 0.00445 -0.1386 0.6958 0.1613
-0.750 0.5871 0.01303 0.00449 -0.1381 0.6890 0.1768
-0.500 0.6130 0.01305 0.00450 -0.1377 0.6823 0.1894
-0.250 0.6387 0.01305 0.00446 -0.1373 0.6757 0.1993
0.000 0.6638 0.01304 0.00442 -0.1367 0.6683 0.2077
0.250 0.6894 0.01301 0.00437 -0.1363 0.6616 0.2151
0.500 0.7139 0.01302 0.00436 -0.1356 0.6538 0.2245
0.750 0.7392 0.01300 0.00434 -0.1351 0.6467 0.2342
1.000 0.7631 0.01300 0.00436 -0.1344 0.6382 0.2438
1.250 0.7878 0.01302 0.00435 -0.1338 0.6305 0.2549
1.500 0.8115 0.01302 0.00439 -0.1330 0.6217 0.2686
2.000 0.8586 0.01302 0.00444 -0.1314 0.6036 0.3096
2.250 0.8794 0.01263 0.00456 -0.1303 0.5940 0.5008
2.750 0.9508 0.01216 0.00479 -0.1337 0.5723 1.0000
3.000 0.9726 0.01233 0.00490 -0.1326 0.5607 1.0000
3.250 0.9942 0.01252 0.00501 -0.1314 0.5490 1.0000
3.500 1.0154 0.01272 0.00513 -0.1301 0.5371 1.0000
3.750 1.0361 0.01295 0.00528 -0.1288 0.5249 1.0000
4.000 1.0567 0.01318 0.00545 -0.1274 0.5130 1.0000
4.250 1.0771 0.01342 0.00563 -0.1261 0.5016 1.0000
4.500 1.0974 0.01368 0.00585 -0.1248 0.4912 1.0000
5.000 1.1373 0.01423 0.00632 -0.1220 0.4717 1.0000
5.250 1.1568 0.01453 0.00658 -0.1206 0.4628 1.0000
5.500 1.1760 0.01483 0.00687 -0.1191 0.4540 1.0000
5.750 1.1948 0.01513 0.00716 -0.1175 0.4463 1.0000
6.000 1.2130 0.01545 0.00747 -0.1159 0.4384 1.0000
6.250 1.2312 0.01578 0.00780 -0.1143 0.4308 1.0000
6.500 1.2489 0.01612 0.00817 -0.1126 0.4230 1.0000
6.750 1.2671 0.01648 0.00854 -0.1110 0.4161 1.0000
7.000 1.2851 0.01683 0.00893 -0.1095 0.4091 1.0000
7.250 1.3027 0.01723 0.00934 -0.1079 0.4025 1.0000
7.500 1.3180 0.01764 0.00980 -0.1059 0.3926 1.0000
7.750 1.3311 0.01810 0.01028 -0.1036 0.3808 1.0000
8.000 1.3418 0.01864 0.01081 -0.1010 0.3661 1.0000
8.250 1.3530 0.01922 0.01138 -0.0985 0.3525 1.0000
8.500 1.3642 0.01983 0.01200 -0.0961 0.3392 1.0000
8.750 1.3750 0.02049 0.01269 -0.0938 0.3266 1.0000
9.000 1.3842 0.02126 0.01346 -0.0913 0.3105 1.0000
9.250 1.3904 0.02220 0.01436 -0.0886 0.2902 1.0000
9.500 1.3928 0.02341 0.01547 -0.0855 0.2671 1.0000
9.750 1.3949 0.02475 0.01672 -0.0826 0.2431 1.0000
10.000 1.3899 0.02663 0.01841 -0.0791 0.2108 1.0000
10.250 1.3803 0.02901 0.02052 -0.0756 0.1677 1.0000
10.500 1.3575 0.03259 0.02363 -0.0713 0.0960 1.0000
10.750 1.3360 0.03642 0.02715 -0.0677 0.0465 1.0000
11.000 1.3316 0.03901 0.02972 -0.0656 0.0287 1.0000
11.250 1.3324 0.04125 0.03200 -0.0641 0.0236 1.0000
11.500 1.3337 0.04352 0.03438 -0.0627 0.0211 1.0000
11.750 1.3359 0.04578 0.03677 -0.0615 0.0193 1.0000
12.000 1.3381 0.04812 0.03924 -0.0605 0.0182 1.0000
12.250 1.3376 0.05082 0.04208 -0.0595 0.0169 1.0000
12.500 1.3358 0.05375 0.04514 -0.0587 0.0162 1.0000
12.750 1.3315 0.05707 0.04861 -0.0580 0.0156 1.0000
13.000 1.3243 0.06089 0.05259 -0.0575 0.0151 1.0000
13.250 1.3164 0.06496 0.05681 -0.0572 0.0147 1.0000
13.500 1.3125 0.06861 0.06061 -0.0572 0.0144 1.0000
13.750 1.3076 0.07251 0.06466 -0.0573 0.0141 1.0000
14.000 1.3022 0.07659 0.06887 -0.0575 0.0137 1.0000
14.250 1.2967 0.08078 0.07319 -0.0579 0.0133 1.0000
14.500 1.2914 0.08499 0.07754 -0.0585 0.0129 1.0000
14.750 1.2866 0.08918 0.08185 -0.0591 0.0124 1.0000
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