GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 500,000 Max Cl/Cd: 88.62 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe628-il-500000.txt Download as CSV file: xf-goe628-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.2159 0.14591 0.14359 -0.0459 1.0000 0.0380
-15.500 -0.6940 0.07051 0.06723 -0.0875 1.0000 0.0429
-15.250 -0.7455 0.06109 0.05762 -0.0941 1.0000 0.0431
-15.000 -0.7446 0.05896 0.05553 -0.0943 1.0000 0.0436
-14.750 -0.7465 0.05658 0.05316 -0.0949 1.0000 0.0439
-14.500 -0.7560 0.05348 0.05005 -0.0961 1.0000 0.0443
-14.250 -0.7829 0.04889 0.04537 -0.0981 1.0000 0.0445
-14.000 -0.8101 0.04523 0.04164 -0.0987 1.0000 0.0447
-13.750 -0.8245 0.04181 0.03815 -0.1013 0.9990 0.0450
-13.500 -0.8048 0.03826 0.03444 -0.1101 0.9937 0.0457
-13.250 -0.7910 0.03586 0.03185 -0.1140 0.9865 0.0466
-13.000 -0.7680 0.03347 0.02918 -0.1186 0.9814 0.0476
-12.750 -0.7502 0.03172 0.02713 -0.1207 0.9745 0.0484
-12.500 -0.7221 0.02986 0.02531 -0.1225 0.9710 0.0493
-12.250 -0.6883 0.02901 0.02447 -0.1247 0.9685 0.0502
-12.000 -0.6534 0.02803 0.02346 -0.1271 0.9665 0.0512
-11.750 -0.6289 0.02699 0.02231 -0.1278 0.9595 0.0521
-11.500 -0.5982 0.02590 0.02104 -0.1297 0.9547 0.0531
-11.250 -0.5646 0.02512 0.02003 -0.1319 0.9507 0.0539
-11.000 -0.5444 0.02340 0.01821 -0.1317 0.9403 0.0548
-10.750 -0.5112 0.02233 0.01717 -0.1333 0.9345 0.0559
-10.500 -0.4876 0.02172 0.01652 -0.1328 0.9227 0.0569
-10.250 -0.4605 0.02117 0.01591 -0.1330 0.9120 0.0581
-10.000 -0.4355 0.02051 0.01511 -0.1327 0.8998 0.0589
-9.750 -0.4133 0.01986 0.01432 -0.1318 0.8856 0.0594
-9.500 -0.3901 0.01925 0.01357 -0.1310 0.8711 0.0598
-9.250 -0.3665 0.01875 0.01292 -0.1302 0.8562 0.0602
-9.000 -0.3434 0.01811 0.01213 -0.1293 0.8412 0.0607
-8.750 -0.3214 0.01712 0.01107 -0.1284 0.8258 0.0613
-8.500 -0.2986 0.01647 0.01035 -0.1274 0.8108 0.0618
-8.250 -0.2753 0.01594 0.00975 -0.1266 0.7974 0.0624
-8.000 -0.2515 0.01550 0.00922 -0.1257 0.7854 0.0629
-7.750 -0.2276 0.01509 0.00874 -0.1249 0.7737 0.0634
-7.500 -0.2033 0.01472 0.00829 -0.1241 0.7636 0.0640
-7.250 -0.1788 0.01438 0.00787 -0.1234 0.7538 0.0647
-7.000 -0.1539 0.01408 0.00749 -0.1227 0.7453 0.0655
-6.750 -0.1289 0.01378 0.00712 -0.1220 0.7366 0.0661
-6.500 -0.1037 0.01352 0.00676 -0.1213 0.7283 0.0667
-6.250 -0.0785 0.01324 0.00644 -0.1206 0.7193 0.0672
-6.000 -0.0536 0.01300 0.00607 -0.1198 0.7099 0.0678
-5.750 -0.0295 0.01258 0.00565 -0.1190 0.7007 0.0688
-5.500 -0.0044 0.01231 0.00531 -0.1183 0.6927 0.0699
-5.250 0.0215 0.01206 0.00504 -0.1178 0.6860 0.0710
-5.000 0.0476 0.01184 0.00479 -0.1172 0.6789 0.0722
-4.750 0.0739 0.01170 0.00455 -0.1167 0.6721 0.0737
-4.500 0.1006 0.01152 0.00435 -0.1162 0.6653 0.0753
-4.250 0.1267 0.01128 0.00410 -0.1157 0.6584 0.0780
-4.000 0.1533 0.01115 0.00391 -0.1152 0.6520 0.0811
-3.750 0.1799 0.01094 0.00374 -0.1147 0.6454 0.0866
-3.500 0.2059 0.01070 0.00355 -0.1142 0.6382 0.1027
-3.250 0.2310 0.01033 0.00335 -0.1136 0.6316 0.1513
-3.000 0.2571 0.01009 0.00327 -0.1131 0.6243 0.1943
-2.750 0.2838 0.01004 0.00323 -0.1127 0.6174 0.2180
-2.500 0.3109 0.01001 0.00321 -0.1123 0.6108 0.2353
-2.250 0.3379 0.00998 0.00321 -0.1119 0.6031 0.2496
-1.750 0.3918 0.01000 0.00318 -0.1110 0.5877 0.2703
-1.500 0.4182 0.01001 0.00318 -0.1104 0.5799 0.2796
-1.250 0.4452 0.01005 0.00318 -0.1100 0.5725 0.2884
-1.000 0.4716 0.01005 0.00319 -0.1095 0.5642 0.2965
-0.750 0.4980 0.01011 0.00320 -0.1090 0.5563 0.3048
-0.500 0.5244 0.01013 0.00321 -0.1084 0.5472 0.3126
-0.250 0.5502 0.01019 0.00324 -0.1078 0.5385 0.3206
0.000 0.5766 0.01025 0.00327 -0.1073 0.5290 0.3284
0.250 0.6018 0.01030 0.00331 -0.1066 0.5200 0.3375
0.500 0.6279 0.01038 0.00336 -0.1060 0.5102 0.3461
0.750 0.6528 0.01043 0.00341 -0.1053 0.5007 0.3542
1.000 0.6780 0.01052 0.00347 -0.1046 0.4899 0.3629
1.250 0.7028 0.01059 0.00352 -0.1038 0.4793 0.3712
1.750 0.7512 0.01082 0.00367 -0.1021 0.4558 0.3876
2.000 0.7746 0.01091 0.00375 -0.1011 0.4446 0.3955
2.250 0.7975 0.01107 0.00385 -0.1000 0.4327 0.4034
2.500 0.8211 0.01117 0.00395 -0.0991 0.4215 0.4118
2.750 0.8435 0.01134 0.00408 -0.0980 0.4108 0.4216
3.000 0.8657 0.01148 0.00421 -0.0968 0.4001 0.4316
3.250 0.8881 0.01164 0.00435 -0.0957 0.3909 0.4429
3.500 0.9095 0.01179 0.00450 -0.0944 0.3822 0.4554
3.750 0.9313 0.01193 0.00467 -0.0932 0.3750 0.4712
4.000 0.9528 0.01205 0.00484 -0.0920 0.3681 0.4921
4.250 0.9716 0.01222 0.00504 -0.0903 0.3617 0.5227
4.500 0.9899 0.01212 0.00525 -0.0884 0.3568 0.6134
4.750 1.0519 0.01187 0.00569 -0.0958 0.3489 1.0000
5.000 1.0699 0.01219 0.00593 -0.0939 0.3436 1.0000
5.250 1.0911 0.01236 0.00610 -0.0926 0.3399 1.0000
5.500 1.1108 0.01257 0.00630 -0.0910 0.3358 1.0000
5.750 1.1294 0.01284 0.00653 -0.0893 0.3319 1.0000
6.000 1.1469 0.01317 0.00680 -0.0874 0.3278 1.0000
6.250 1.1668 0.01344 0.00706 -0.0860 0.3244 1.0000
6.500 1.1872 0.01365 0.00730 -0.0847 0.3211 1.0000
6.750 1.2067 0.01392 0.00756 -0.0832 0.3176 1.0000
7.000 1.2256 0.01423 0.00784 -0.0817 0.3143 1.0000
7.250 1.2437 0.01462 0.00819 -0.0801 0.3110 1.0000
7.500 1.2633 0.01497 0.00854 -0.0788 0.3080 1.0000
7.750 1.2833 0.01523 0.00884 -0.0776 0.3054 1.0000
8.000 1.3025 0.01553 0.00916 -0.0763 0.3024 1.0000
8.250 1.3214 0.01586 0.00950 -0.0750 0.2995 1.0000
8.500 1.3395 0.01625 0.00988 -0.0736 0.2967 1.0000
8.750 1.3575 0.01674 0.01033 -0.0722 0.2934 1.0000
9.000 1.3761 0.01712 0.01074 -0.0710 0.2905 1.0000
9.250 1.3938 0.01746 0.01114 -0.0696 0.2875 1.0000
9.500 1.4112 0.01785 0.01156 -0.0683 0.2841 1.0000
9.750 1.4279 0.01831 0.01202 -0.0669 0.2810 1.0000
10.000 1.4441 0.01885 0.01254 -0.0655 0.2779 1.0000
10.250 1.4617 0.01941 0.01309 -0.0643 0.2749 1.0000
10.500 1.4788 0.01986 0.01363 -0.0632 0.2729 1.0000
10.750 1.4957 0.02035 0.01418 -0.0620 0.2704 1.0000
11.000 1.5119 0.02090 0.01477 -0.0608 0.2677 1.0000
11.250 1.5273 0.02150 0.01540 -0.0596 0.2649 1.0000
11.500 1.5418 0.02219 0.01608 -0.0583 0.2620 1.0000
11.750 1.5576 0.02290 0.01678 -0.0572 0.2589 1.0000
12.000 1.5724 0.02356 0.01753 -0.0561 0.2569 1.0000
12.250 1.5871 0.02427 0.01832 -0.0550 0.2543 1.0000
12.500 1.6008 0.02505 0.01916 -0.0539 0.2514 1.0000
12.750 1.6137 0.02590 0.02004 -0.0529 0.2485 1.0000
13.000 1.6256 0.02686 0.02099 -0.0517 0.2455 1.0000
13.250 1.6382 0.02780 0.02197 -0.0507 0.2424 1.0000
13.500 1.6497 0.02883 0.02311 -0.0498 0.2393 1.0000
13.750 1.6605 0.02995 0.02430 -0.0489 0.2356 1.0000
14.000 1.6691 0.03125 0.02562 -0.0480 0.2317 1.0000
14.250 1.6767 0.03266 0.02703 -0.0469 0.2274 1.0000
14.500 1.6871 0.03397 0.02845 -0.0463 0.2239 1.0000
14.750 1.6959 0.03540 0.02995 -0.0457 0.2200 1.0000
15.000 1.7015 0.03712 0.03167 -0.0449 0.2159 1.0000
15.250 1.7070 0.03887 0.03347 -0.0442 0.2118 1.0000
15.500 1.7147 0.04054 0.03524 -0.0437 0.2073 1.0000
15.750 1.7189 0.04251 0.03725 -0.0431 0.2029 1.0000
16.000 1.7191 0.04485 0.03958 -0.0425 0.1985 1.0000
16.250 1.7251 0.04677 0.04162 -0.0421 0.1938 1.0000
16.500 1.7266 0.04913 0.04402 -0.0417 0.1892 1.0000
16.750 1.7230 0.05201 0.04691 -0.0413 0.1844 1.0000
17.000 1.7260 0.05432 0.04932 -0.0411 0.1796 1.0000
17.250 1.7219 0.05739 0.05242 -0.0409 0.1745 1.0000
17.500 1.7166 0.06064 0.05572 -0.0407 0.1695 1.0000
17.750 1.7142 0.06364 0.05879 -0.0407 0.1645 1.0000
18.000 1.7020 0.06777 0.06293 -0.0408 0.1590 1.0000
18.250 1.6978 0.07106 0.06629 -0.0409 0.1543 1.0000
18.500 1.6883 0.07502 0.07032 -0.0412 0.1496 1.0000
18.750 1.6740 0.07962 0.07493 -0.0417 0.1450 1.0000
19.000 1.6663 0.08347 0.07887 -0.0422 0.1404 1.0000
19.250 1.6520 0.08821 0.08365 -0.0429 0.1360 1.0000
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