GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 200,000 Max Cl/Cd: 78.16 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe693-il-200000.txt Download as CSV file: xf-goe693-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3912 0.08866 0.08519 -0.0399 1.0000 0.0846
-8.250 -0.4121 0.08674 0.08336 -0.0376 1.0000 0.0859
-8.000 -0.4430 0.08558 0.08233 -0.0336 1.0000 0.0865
-7.750 -0.5050 0.05371 0.04979 -0.0655 0.9854 0.0672
-7.500 -0.4796 0.04894 0.04487 -0.0691 0.9811 0.0646
-7.250 -0.4659 0.04032 0.03565 -0.0736 0.9734 0.0636
-7.000 -0.4426 0.03304 0.02756 -0.0773 0.9694 0.0633
-6.750 -0.4193 0.02916 0.02306 -0.0782 0.9615 0.0643
-6.500 -0.3842 0.02674 0.02004 -0.0805 0.9579 0.0662
-6.250 -0.3473 0.02415 0.01719 -0.0833 0.9557 0.0681
-6.000 -0.3179 0.02311 0.01605 -0.0839 0.9477 0.0700
-5.750 -0.2791 0.02204 0.01482 -0.0863 0.9443 0.0729
-5.500 -0.2397 0.02101 0.01349 -0.0887 0.9415 0.0765
-5.250 -0.2107 0.01980 0.01219 -0.0891 0.9341 0.0795
-5.000 -0.1759 0.01913 0.01150 -0.0905 0.9290 0.0835
-4.750 -0.1387 0.01850 0.01068 -0.0921 0.9255 0.0892
-4.500 -0.1128 0.01779 0.01003 -0.0919 0.9164 0.0951
-4.250 -0.0793 0.01737 0.00945 -0.0927 0.9114 0.1031
-4.000 -0.0519 0.01667 0.00884 -0.0926 0.9040 0.1120
-3.750 -0.0226 0.01612 0.00826 -0.0928 0.8974 0.1228
-3.500 0.0069 0.01579 0.00785 -0.0929 0.8913 0.1340
-3.250 0.0336 0.01539 0.00751 -0.0927 0.8834 0.1447
-3.000 0.0634 0.01494 0.00706 -0.0929 0.8785 0.1556
-2.750 0.0891 0.01475 0.00684 -0.0924 0.8696 0.1662
-2.500 0.1179 0.01441 0.00652 -0.0924 0.8641 0.1777
-2.250 0.1440 0.01414 0.00630 -0.0920 0.8561 0.1888
-2.000 0.1719 0.01381 0.00599 -0.0918 0.8494 0.2017
-1.750 0.1983 0.01355 0.00578 -0.0914 0.8412 0.2176
-1.500 0.2255 0.01318 0.00550 -0.0910 0.8337 0.2408
-1.250 0.2509 0.01277 0.00533 -0.0905 0.8253 0.2880
-1.000 0.2740 0.01187 0.00515 -0.0897 0.8179 0.4659
-0.750 0.2886 0.01080 0.00531 -0.0860 0.8098 0.8049
-0.500 0.3613 0.01063 0.00523 -0.0940 0.8030 0.9859
-0.250 0.4062 0.01064 0.00510 -0.0976 0.7952 1.0000
0.000 0.4311 0.01067 0.00500 -0.0969 0.7871 1.0000
0.250 0.4558 0.01074 0.00497 -0.0962 0.7790 1.0000
0.500 0.4811 0.01078 0.00490 -0.0955 0.7708 1.0000
0.750 0.5058 0.01086 0.00490 -0.0948 0.7625 1.0000
1.000 0.5313 0.01092 0.00487 -0.0942 0.7546 1.0000
1.250 0.5562 0.01102 0.00491 -0.0935 0.7464 1.0000
1.500 0.5819 0.01109 0.00489 -0.0929 0.7385 1.0000
1.750 0.6068 0.01119 0.00496 -0.0922 0.7299 1.0000
2.000 0.6328 0.01126 0.00494 -0.0916 0.7217 1.0000
2.250 0.6576 0.01137 0.00504 -0.0909 0.7125 1.0000
2.500 0.6842 0.01145 0.00503 -0.0905 0.7048 1.0000
2.750 0.7090 0.01156 0.00516 -0.0898 0.6953 1.0000
3.000 0.7356 0.01165 0.00519 -0.0894 0.6873 1.0000
3.250 0.7605 0.01175 0.00529 -0.0887 0.6768 1.0000
3.500 0.7861 0.01184 0.00537 -0.0881 0.6666 1.0000
3.750 0.8124 0.01191 0.00538 -0.0876 0.6563 1.0000
4.000 0.8370 0.01198 0.00547 -0.0868 0.6432 1.0000
4.250 0.8618 0.01205 0.00554 -0.0861 0.6292 1.0000
4.500 0.8866 0.01213 0.00560 -0.0853 0.6144 1.0000
4.750 0.9111 0.01222 0.00568 -0.0845 0.5981 1.0000
5.000 0.9354 0.01233 0.00575 -0.0836 0.5803 1.0000
5.250 0.9593 0.01247 0.00585 -0.0827 0.5614 1.0000
5.500 0.9826 0.01265 0.00602 -0.0818 0.5397 1.0000
5.750 1.0055 0.01288 0.00617 -0.0808 0.5174 1.0000
6.000 1.0278 0.01315 0.00639 -0.0797 0.4934 1.0000
6.250 1.0492 0.01351 0.00663 -0.0784 0.4697 1.0000
6.500 1.0707 0.01389 0.00695 -0.0773 0.4475 1.0000
6.750 1.0920 0.01431 0.00730 -0.0761 0.4280 1.0000
7.000 1.1127 0.01477 0.00768 -0.0749 0.4092 1.0000
7.250 1.1330 0.01527 0.00811 -0.0736 0.3913 1.0000
7.500 1.1532 0.01575 0.00856 -0.0724 0.3739 1.0000
7.750 1.1726 0.01625 0.00905 -0.0710 0.3556 1.0000
8.000 1.1908 0.01680 0.00957 -0.0694 0.3358 1.0000
8.250 1.2066 0.01742 0.01011 -0.0675 0.3141 1.0000
8.500 1.2222 0.01798 0.01065 -0.0656 0.2893 1.0000
8.750 1.2360 0.01861 0.01120 -0.0634 0.2651 1.0000
9.000 1.2499 0.01923 0.01178 -0.0613 0.2418 1.0000
9.250 1.2603 0.01994 0.01242 -0.0586 0.2231 1.0000
9.500 1.2703 0.02074 0.01315 -0.0559 0.2069 1.0000
9.750 1.2794 0.02166 0.01400 -0.0533 0.1926 1.0000
10.000 1.2884 0.02266 0.01495 -0.0508 0.1805 1.0000
10.250 1.2992 0.02361 0.01593 -0.0487 0.1692 1.0000
10.500 1.3094 0.02462 0.01699 -0.0466 0.1581 1.0000
10.750 1.3189 0.02570 0.01808 -0.0446 0.1464 1.0000
11.000 1.3311 0.02662 0.01908 -0.0430 0.1306 1.0000
11.250 1.3402 0.02780 0.02018 -0.0412 0.1025 1.0000
11.500 1.3360 0.03009 0.02223 -0.0384 0.0785 1.0000
11.750 1.3308 0.03261 0.02466 -0.0357 0.0628 1.0000
12.000 1.3317 0.03475 0.02679 -0.0338 0.0533 1.0000
12.250 1.3342 0.03682 0.02892 -0.0321 0.0481 1.0000
12.500 1.3322 0.03936 0.03146 -0.0305 0.0450 1.0000
12.750 1.3329 0.04172 0.03392 -0.0292 0.0426 1.0000
13.000 1.3338 0.04413 0.03643 -0.0280 0.0406 1.0000
13.250 1.3323 0.04683 0.03917 -0.0269 0.0389 1.0000
13.500 1.3262 0.05000 0.04235 -0.0257 0.0374 1.0000
13.750 1.3284 0.05246 0.04495 -0.0249 0.0362 1.0000
14.000 1.3297 0.05505 0.04766 -0.0241 0.0351 1.0000
14.250 1.3308 0.05769 0.05038 -0.0234 0.0341 1.0000
14.500 1.3321 0.06033 0.05308 -0.0227 0.0332 1.0000
14.750 1.3340 0.06291 0.05570 -0.0219 0.0324 1.0000
15.000 1.3377 0.06520 0.05798 -0.0207 0.0315 1.0000
15.250 1.3427 0.06752 0.06038 -0.0196 0.0308 1.0000
15.500 1.3451 0.07026 0.06330 -0.0193 0.0301 1.0000
15.750 1.3470 0.07311 0.06630 -0.0190 0.0294 1.0000
16.000 1.3487 0.07599 0.06932 -0.0188 0.0287 1.0000
16.250 1.3497 0.07901 0.07247 -0.0187 0.0281 1.0000
16.500 1.3505 0.08208 0.07566 -0.0187 0.0276 1.0000
16.750 1.3517 0.08516 0.07885 -0.0187 0.0272 1.0000
17.000 1.3524 0.08833 0.08212 -0.0188 0.0268 1.0000
17.250 1.3529 0.09156 0.08545 -0.0188 0.0264 1.0000
17.500 1.3529 0.09497 0.08898 -0.0187 0.0261 1.0000
17.750 1.3482 0.09924 0.09342 -0.0192 0.0259 1.0000
18.000 1.3384 0.10434 0.09872 -0.0206 0.0258 1.0000
18.250 1.3253 0.11003 0.10461 -0.0228 0.0257 1.0000
18.500 1.3103 0.11621 0.11102 -0.0258 0.0257 1.0000
18.750 1.2947 0.12281 0.11783 -0.0293 0.0257 1.0000
19.000 1.2781 0.12990 0.12514 -0.0334 0.0257 1.0000
19.250 1.2603 0.13764 0.13310 -0.0385 0.0258 1.0000
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