GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 620 AIRFOIL (goe620-il) Reynolds number: 100,000 Max Cl/Cd: 43.12 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe620-il-100000-n5.txt Download as CSV file: xf-goe620-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 620 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0731 0.09914 0.09338 -0.1063 0.9272 0.0630
-10.750 -0.0671 0.09384 0.08805 -0.1110 0.9235 0.0635
-10.500 -0.0664 0.08733 0.08151 -0.1168 0.9199 0.0644
-10.000 -0.2607 0.04902 0.04263 -0.1459 0.8882 0.0632
-9.750 -0.2954 0.04535 0.03862 -0.1441 0.8751 0.0632
-9.500 -0.2998 0.04182 0.03469 -0.1448 0.8689 0.0637
-9.250 -0.3091 0.04003 0.03262 -0.1415 0.8591 0.0641
-9.000 -0.3024 0.03773 0.02993 -0.1407 0.8534 0.0650
-8.750 -0.2842 0.03569 0.02753 -0.1412 0.8501 0.0661
-8.500 -0.2798 0.03512 0.02696 -0.1378 0.8415 0.0669
-8.250 -0.2601 0.03409 0.02584 -0.1373 0.8368 0.0680
-8.000 -0.2350 0.03284 0.02443 -0.1377 0.8335 0.0693
-7.750 -0.2144 0.03170 0.02309 -0.1371 0.8292 0.0705
-7.500 -0.2073 0.03102 0.02226 -0.1340 0.8213 0.0715
-7.250 -0.1832 0.02990 0.02089 -0.1338 0.8172 0.0728
-7.000 -0.1537 0.02892 0.01987 -0.1345 0.8144 0.0746
-6.750 -0.1392 0.02850 0.01943 -0.1324 0.8082 0.0761
-6.500 -0.1228 0.02801 0.01887 -0.1306 0.8022 0.0779
-6.250 -0.0956 0.02722 0.01794 -0.1306 0.7985 0.0802
-6.000 -0.0645 0.02638 0.01699 -0.1313 0.7957 0.0824
-5.750 -0.0521 0.02612 0.01675 -0.1288 0.7893 0.0841
-5.500 -0.0339 0.02575 0.01634 -0.1271 0.7834 0.0868
-5.250 -0.0051 0.02516 0.01561 -0.1273 0.7798 0.0908
-5.000 0.0266 0.02451 0.01497 -0.1280 0.7770 0.0948
-4.750 0.0373 0.02439 0.01482 -0.1250 0.7700 0.0984
-4.500 0.0571 0.02404 0.01445 -0.1236 0.7644 0.1033
-4.250 0.0866 0.02352 0.01389 -0.1239 0.7608 0.1116
-4.000 0.1200 0.02289 0.01328 -0.1248 0.7580 0.1235
-3.750 0.1270 0.02292 0.01337 -0.1212 0.7501 0.1330
-3.500 0.1502 0.02263 0.01313 -0.1203 0.7449 0.1500
-3.250 0.1821 0.02225 0.01277 -0.1209 0.7414 0.1731
-3.000 0.2188 0.02187 0.01237 -0.1224 0.7387 0.1970
-2.750 0.2214 0.02217 0.01272 -0.1179 0.7296 0.2089
-2.500 0.2487 0.02201 0.01254 -0.1177 0.7249 0.2279
-2.250 0.2832 0.02173 0.01225 -0.1187 0.7216 0.2495
-2.000 0.3034 0.02176 0.01230 -0.1172 0.7157 0.2686
-1.750 0.3176 0.02189 0.01246 -0.1147 0.7085 0.2857
-1.500 0.3488 0.02169 0.01227 -0.1151 0.7043 0.3075
-1.250 0.3865 0.02139 0.01194 -0.1166 0.7012 0.3287
-1.000 0.3884 0.02177 0.01235 -0.1120 0.6920 0.3401
-0.750 0.4159 0.02164 0.01221 -0.1117 0.6869 0.3576
-0.500 0.4526 0.02134 0.01190 -0.1130 0.6834 0.3784
-0.250 0.4601 0.02160 0.01224 -0.1094 0.6751 0.3928
0.000 0.4830 0.02154 0.01223 -0.1083 0.6692 0.4132
0.500 0.5290 0.02148 0.01224 -0.1063 0.6576 0.4583
0.750 0.5498 0.02147 0.01230 -0.1049 0.6511 0.4823
1.000 0.5878 0.02118 0.01205 -0.1064 0.6472 0.5163
1.250 0.5945 0.02145 0.01242 -0.1026 0.6390 0.5432
1.500 0.6174 0.02139 0.01245 -0.1016 0.6327 0.5822
1.750 0.6562 0.02098 0.01215 -0.1031 0.6287 0.6381
2.000 0.6598 0.02127 0.01269 -0.0988 0.6199 0.6954
2.500 0.7843 0.02062 0.01228 -0.1117 0.6093 1.0000
2.750 0.7834 0.02111 0.01272 -0.1066 0.5994 1.0000
3.000 0.8199 0.02084 0.01227 -0.1078 0.5930 1.0000
3.250 0.8208 0.02134 0.01275 -0.1031 0.5827 1.0000
3.500 0.8543 0.02114 0.01238 -0.1038 0.5758 1.0000
3.750 0.8598 0.02165 0.01287 -0.1000 0.5663 1.0000
4.000 0.8878 0.02165 0.01275 -0.0999 0.5596 1.0000
4.250 0.9018 0.02204 0.01310 -0.0976 0.5517 1.0000
4.500 0.9222 0.02228 0.01326 -0.0963 0.5443 1.0000
4.750 0.9483 0.02239 0.01328 -0.0960 0.5379 1.0000
5.000 0.9591 0.02292 0.01380 -0.0933 0.5296 1.0000
5.250 0.9888 0.02293 0.01369 -0.0935 0.5232 1.0000
5.500 0.9972 0.02356 0.01433 -0.0906 0.5144 1.0000
5.750 1.0203 0.02374 0.01442 -0.0898 0.5066 1.0000
6.000 1.0334 0.02427 0.01493 -0.0877 0.4982 1.0000
6.250 1.0509 0.02464 0.01525 -0.0861 0.4899 1.0000
6.500 1.0665 0.02511 0.01568 -0.0844 0.4814 1.0000
6.750 1.0800 0.02564 0.01619 -0.0825 0.4724 1.0000
7.000 1.0972 0.02609 0.01659 -0.0810 0.4646 1.0000
7.250 1.1075 0.02680 0.01731 -0.0788 0.4556 1.0000
7.500 1.1275 0.02716 0.01760 -0.0778 0.4482 1.0000
7.750 1.1344 0.02808 0.01858 -0.0753 0.4395 1.0000
8.000 1.1562 0.02837 0.01878 -0.0745 0.4326 1.0000
8.250 1.1609 0.02947 0.01996 -0.0720 0.4237 1.0000
8.500 1.1780 0.02999 0.02043 -0.0707 0.4164 1.0000
8.750 1.1862 0.03098 0.02146 -0.0687 0.4081 1.0000
9.000 1.1991 0.03175 0.02221 -0.0672 0.4004 1.0000
9.250 1.2110 0.03261 0.02308 -0.0656 0.3928 1.0000
9.500 1.2198 0.03366 0.02416 -0.0638 0.3849 1.0000
9.750 1.2372 0.03423 0.02467 -0.0628 0.3787 1.0000
10.000 1.2419 0.03563 0.02617 -0.0609 0.3710 1.0000
10.250 1.2562 0.03640 0.02692 -0.0597 0.3645 1.0000
10.500 1.2641 0.03764 0.02821 -0.0581 0.3574 1.0000
10.750 1.2725 0.03885 0.02945 -0.0566 0.3503 1.0000
11.000 1.2849 0.03978 0.03035 -0.0554 0.3436 1.0000
11.250 1.2877 0.04147 0.03213 -0.0538 0.3359 1.0000
11.500 1.3013 0.04233 0.03295 -0.0527 0.3298 1.0000
11.750 1.3049 0.04408 0.03479 -0.0512 0.3231 1.0000
12.000 1.3125 0.04551 0.03626 -0.0500 0.3172 1.0000
12.250 1.3270 0.04634 0.03706 -0.0491 0.3119 1.0000
12.500 1.3260 0.04861 0.03946 -0.0477 0.3051 1.0000
12.750 1.3336 0.05009 0.04097 -0.0467 0.2990 1.0000
13.000 1.3432 0.05142 0.04231 -0.0457 0.2937 1.0000
13.250 1.3430 0.05378 0.04479 -0.0446 0.2878 1.0000
13.500 1.3507 0.05533 0.04639 -0.0437 0.2824 1.0000
13.750 1.3605 0.05672 0.04778 -0.0429 0.2774 1.0000
14.000 1.3567 0.05958 0.05080 -0.0420 0.2714 1.0000
14.250 1.3620 0.06146 0.05272 -0.0413 0.2659 1.0000
14.500 1.3720 0.06284 0.05410 -0.0406 0.2608 1.0000
14.750 1.3638 0.06637 0.05782 -0.0400 0.2545 1.0000
15.000 1.3672 0.06855 0.06004 -0.0394 0.2487 1.0000
15.250 1.3729 0.07049 0.06200 -0.0389 0.2430 1.0000
15.500 1.3621 0.07455 0.06622 -0.0387 0.2361 1.0000
15.750 1.3690 0.07634 0.06800 -0.0383 0.2301 1.0000
16.000 1.3606 0.08023 0.07202 -0.0382 0.2234 1.0000
16.250 1.3553 0.08376 0.07564 -0.0382 0.2166 1.0000
16.500 1.3648 0.08526 0.07711 -0.0379 0.2112 1.0000
16.750 1.3473 0.09066 0.08270 -0.0385 0.2040 1.0000
17.000 1.3518 0.09291 0.08497 -0.0385 0.1986 1.0000
17.250 1.3481 0.09644 0.08858 -0.0389 0.1933 1.0000
17.500 1.3370 0.10113 0.09339 -0.0397 0.1875 1.0000
17.750 1.3452 0.10288 0.09515 -0.0397 0.1833 1.0000
18.000 1.3337 0.10772 0.10010 -0.0407 0.1783 1.0000
18.250 1.3228 0.11254 0.10504 -0.0419 0.1734 1.0000
18.500 1.3319 0.11417 0.10666 -0.0421 0.1698 1.0000
18.750 1.3208 0.11913 0.11172 -0.0435 0.1657 1.0000
19.000 1.3039 0.12511 0.11784 -0.0456 0.1613 1.0000
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Polar data table (+)
Polar graphs
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