GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.77 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe449-il-1000000-n5.txt Download as CSV file: xf-goe449-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.6137 0.09809 0.09559 -0.0975 0.9907 0.0228
-17.750 -0.6643 0.08564 0.08296 -0.1057 0.9883 0.0229
-17.500 -0.7182 0.07343 0.07058 -0.1144 0.9852 0.0230
-17.250 -0.7791 0.06031 0.05726 -0.1243 0.9808 0.0229
-17.000 -0.8279 0.04843 0.04515 -0.1338 0.9735 0.0229
-16.750 -0.8458 0.03984 0.03633 -0.1432 0.9677 0.0229
-16.500 -0.8426 0.03472 0.03104 -0.1500 0.9602 0.0231
-16.250 -0.8285 0.03119 0.02735 -0.1559 0.9537 0.0233
-16.000 -0.8079 0.02861 0.02463 -0.1608 0.9455 0.0234
-15.750 -0.7772 0.02649 0.02236 -0.1666 0.9399 0.0236
-15.500 -0.7479 0.02488 0.02061 -0.1709 0.9304 0.0237
-15.250 -0.7189 0.02360 0.01920 -0.1743 0.9204 0.0239
-15.000 -0.7042 0.02210 0.01755 -0.1757 0.9060 0.0242
-14.750 -0.6937 0.02115 0.01648 -0.1748 0.8926 0.0244
-14.500 -0.6858 0.02033 0.01556 -0.1731 0.8808 0.0246
-14.250 -0.6771 0.01968 0.01480 -0.1710 0.8704 0.0248
-14.000 -0.6696 0.01905 0.01409 -0.1685 0.8606 0.0249
-13.750 -0.6601 0.01854 0.01349 -0.1660 0.8522 0.0251
-13.500 -0.6504 0.01805 0.01293 -0.1634 0.8440 0.0253
-13.250 -0.6413 0.01760 0.01238 -0.1606 0.8362 0.0254
-13.000 -0.6310 0.01717 0.01189 -0.1578 0.8295 0.0256
-12.750 -0.6202 0.01682 0.01147 -0.1551 0.8230 0.0258
-12.500 -0.6059 0.01650 0.01108 -0.1529 0.8176 0.0261
-12.250 -0.5895 0.01613 0.01065 -0.1511 0.8126 0.0263
-12.000 -0.5723 0.01578 0.01024 -0.1494 0.8070 0.0266
-11.500 -0.5361 0.01512 0.00944 -0.1462 0.7958 0.0270
-11.250 -0.5169 0.01481 0.00906 -0.1448 0.7899 0.0272
-11.000 -0.4974 0.01452 0.00870 -0.1434 0.7842 0.0274
-10.750 -0.4764 0.01424 0.00836 -0.1422 0.7801 0.0276
-10.500 -0.4567 0.01386 0.00794 -0.1409 0.7757 0.0279
-10.250 -0.4366 0.01351 0.00754 -0.1396 0.7708 0.0282
-10.000 -0.4159 0.01323 0.00719 -0.1384 0.7660 0.0286
-9.750 -0.3937 0.01294 0.00688 -0.1374 0.7618 0.0289
-9.500 -0.3711 0.01268 0.00659 -0.1365 0.7572 0.0293
-9.250 -0.3485 0.01244 0.00630 -0.1355 0.7525 0.0297
-9.000 -0.3257 0.01224 0.00605 -0.1346 0.7480 0.0302
-8.750 -0.3020 0.01201 0.00579 -0.1338 0.7444 0.0306
-8.500 -0.2780 0.01180 0.00555 -0.1331 0.7406 0.0310
-8.250 -0.2540 0.01160 0.00531 -0.1324 0.7366 0.0314
-8.000 -0.2301 0.01142 0.00508 -0.1316 0.7328 0.0317
-7.750 -0.2068 0.01119 0.00482 -0.1307 0.7294 0.0324
-7.500 -0.1821 0.01098 0.00460 -0.1301 0.7265 0.0331
-7.250 -0.1574 0.01078 0.00440 -0.1295 0.7230 0.0338
-7.000 -0.1327 0.01062 0.00421 -0.1289 0.7191 0.0346
-6.750 -0.1082 0.01047 0.00403 -0.1282 0.7150 0.0355
-6.500 -0.0837 0.01033 0.00386 -0.1275 0.7111 0.0363
-6.250 -0.0585 0.01015 0.00368 -0.1270 0.7075 0.0377
-6.000 -0.0334 0.01000 0.00353 -0.1264 0.7036 0.0392
-5.750 -0.0085 0.00987 0.00338 -0.1258 0.6995 0.0411
-5.500 0.0158 0.00974 0.00324 -0.1250 0.6954 0.0438
-5.250 0.0412 0.00961 0.00311 -0.1245 0.6918 0.0467
-5.000 0.0664 0.00947 0.00299 -0.1240 0.6874 0.0504
-4.750 0.0911 0.00937 0.00288 -0.1233 0.6822 0.0542
-4.500 0.1153 0.00929 0.00279 -0.1225 0.6768 0.0582
-4.250 0.1408 0.00918 0.00270 -0.1220 0.6718 0.0620
-4.000 0.1658 0.00910 0.00261 -0.1214 0.6661 0.0657
-3.750 0.1896 0.00904 0.00253 -0.1205 0.6603 0.0694
-3.500 0.2149 0.00896 0.00246 -0.1200 0.6544 0.0731
-3.250 0.2388 0.00891 0.00239 -0.1191 0.6465 0.0768
-3.000 0.2625 0.00886 0.00233 -0.1182 0.6387 0.0807
-2.750 0.2860 0.00884 0.00228 -0.1173 0.6294 0.0839
-2.500 0.3091 0.00880 0.00223 -0.1163 0.6208 0.0880
-2.250 0.3310 0.00879 0.00219 -0.1150 0.6099 0.0923
-2.000 0.3533 0.00879 0.00216 -0.1139 0.5986 0.0968
-1.750 0.3741 0.00878 0.00213 -0.1124 0.5876 0.1043
-1.500 0.3946 0.00878 0.00212 -0.1109 0.5767 0.1137
-1.250 0.4160 0.00877 0.00211 -0.1095 0.5677 0.1237
-0.750 0.4543 0.00874 0.00210 -0.1059 0.5510 0.1492
-0.500 0.4733 0.00873 0.00210 -0.1041 0.5437 0.1648
-0.250 0.4931 0.00871 0.00212 -0.1025 0.5375 0.1851
0.000 0.5142 0.00868 0.00214 -0.1011 0.5319 0.2061
0.250 0.5337 0.00868 0.00218 -0.0994 0.5261 0.2286
0.500 0.5538 0.00868 0.00223 -0.0979 0.5213 0.2540
0.750 0.5756 0.00866 0.00228 -0.0967 0.5168 0.2823
1.000 0.5964 0.00865 0.00234 -0.0953 0.5120 0.3149
1.250 0.6151 0.00863 0.00243 -0.0936 0.5071 0.3621
1.500 0.6335 0.00853 0.00254 -0.0918 0.5032 0.4431
1.750 0.6549 0.00851 0.00262 -0.0905 0.4992 0.4833
2.000 0.6743 0.00852 0.00271 -0.0889 0.4936 0.5215
2.250 0.6849 0.00833 0.00288 -0.0856 0.4874 0.6541
2.500 0.7016 0.00824 0.00299 -0.0833 0.4827 0.7255
2.750 0.7111 0.00804 0.00317 -0.0794 0.4774 0.8415
3.000 0.7340 0.00806 0.00338 -0.0783 0.4723 0.9250
3.250 0.7816 0.00823 0.00355 -0.0828 0.4678 0.9555
3.500 0.8333 0.00838 0.00370 -0.0882 0.4635 0.9676
3.750 0.8788 0.00857 0.00386 -0.0923 0.4572 0.9737
4.000 0.9148 0.00879 0.00403 -0.0944 0.4502 0.9798
4.250 0.9525 0.00894 0.00417 -0.0968 0.4452 0.9854
4.500 0.9850 0.00914 0.00434 -0.0982 0.4383 0.9921
4.750 1.0124 0.00940 0.00456 -0.0985 0.4319 1.0000
5.000 1.0277 0.00955 0.00470 -0.0962 0.4262 1.0000
5.250 1.0431 0.00975 0.00487 -0.0940 0.4200 1.0000
5.500 1.0601 0.00995 0.00505 -0.0921 0.4146 1.0000
5.750 1.0777 0.01016 0.00525 -0.0903 0.4077 1.0000
6.000 1.0935 0.01045 0.00550 -0.0884 0.3999 1.0000
6.250 1.1097 0.01076 0.00577 -0.0865 0.3887 1.0000
6.500 1.1244 0.01114 0.00609 -0.0844 0.3767 1.0000
6.750 1.1389 0.01155 0.00644 -0.0823 0.3648 1.0000
7.000 1.1546 0.01195 0.00681 -0.0805 0.3546 1.0000
7.250 1.1704 0.01238 0.00719 -0.0788 0.3439 1.0000
7.500 1.1837 0.01291 0.00767 -0.0767 0.3309 1.0000
7.750 1.1969 0.01349 0.00818 -0.0747 0.3171 1.0000
8.000 1.2118 0.01402 0.00867 -0.0731 0.3063 1.0000
8.250 1.2272 0.01456 0.00917 -0.0715 0.2968 1.0000
8.750 1.2564 0.01574 0.01029 -0.0683 0.2773 1.0000
9.000 1.2706 0.01639 0.01090 -0.0668 0.2685 1.0000
9.250 1.2860 0.01700 0.01149 -0.0654 0.2606 1.0000
9.500 1.2998 0.01770 0.01217 -0.0639 0.2523 1.0000
9.750 1.3149 0.01836 0.01282 -0.0626 0.2451 1.0000
10.000 1.3274 0.01916 0.01359 -0.0611 0.2369 1.0000
10.250 1.3412 0.01993 0.01434 -0.0597 0.2284 1.0000
10.500 1.3533 0.02081 0.01519 -0.0582 0.2213 1.0000
10.750 1.3670 0.02162 0.01600 -0.0570 0.2134 1.0000
11.000 1.3778 0.02261 0.01696 -0.0555 0.2060 1.0000
11.250 1.3906 0.02350 0.01785 -0.0542 0.1980 1.0000
11.500 1.3986 0.02472 0.01903 -0.0525 0.1872 1.0000
11.750 1.4104 0.02573 0.02003 -0.0513 0.1799 1.0000
12.000 1.4200 0.02691 0.02119 -0.0499 0.1723 1.0000
12.250 1.4262 0.02833 0.02257 -0.0483 0.1611 1.0000
12.500 1.4296 0.03000 0.02416 -0.0465 0.1473 1.0000
12.750 1.4349 0.03158 0.02571 -0.0450 0.1375 1.0000
13.000 1.4433 0.03295 0.02708 -0.0438 0.1317 1.0000
13.250 1.4459 0.03481 0.02890 -0.0422 0.1228 1.0000
13.500 1.4557 0.03613 0.03025 -0.0413 0.1193 1.0000
13.750 1.4653 0.03752 0.03167 -0.0404 0.1169 1.0000
14.000 1.4736 0.03901 0.03318 -0.0395 0.1137 1.0000
14.250 1.4782 0.04085 0.03503 -0.0383 0.1089 1.0000
14.500 1.4879 0.04227 0.03648 -0.0376 0.1068 1.0000
14.750 1.4956 0.04389 0.03815 -0.0368 0.1045 1.0000
15.000 1.5016 0.04569 0.03996 -0.0360 0.1009 1.0000
15.250 1.5071 0.04758 0.04188 -0.0352 0.0987 1.0000
15.500 1.5142 0.04932 0.04367 -0.0346 0.0958 1.0000
15.750 1.5205 0.05117 0.04555 -0.0339 0.0930 1.0000
16.000 1.5228 0.05340 0.04779 -0.0332 0.0885 1.0000
16.250 1.5269 0.05551 0.04993 -0.0326 0.0850 1.0000
16.500 1.5241 0.05834 0.05274 -0.0319 0.0769 1.0000
16.750 1.5257 0.06077 0.05519 -0.0314 0.0723 1.0000
17.000 1.5222 0.06373 0.05814 -0.0308 0.0657 1.0000
17.500 1.5185 0.06949 0.06394 -0.0300 0.0578 1.0000
17.750 1.5146 0.07263 0.06710 -0.0297 0.0537 1.0000
18.000 1.5128 0.07561 0.07012 -0.0295 0.0504 1.0000
18.250 1.5094 0.07874 0.07329 -0.0294 0.0475 1.0000
18.500 1.5057 0.08196 0.07653 -0.0293 0.0434 1.0000
18.750 1.5016 0.08529 0.07990 -0.0293 0.0409 1.0000
19.000 1.4961 0.08878 0.08340 -0.0294 0.0361 1.0000
19.250 1.4855 0.09295 0.08758 -0.0296 0.0298 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 449 AIRFOIL (goe449-il)