GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 200,000 Max Cl/Cd: 78.66 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe682-il-200000.txt Download as CSV file: xf-goe682-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3563 0.08919 0.08593 -0.0311 1.0000 0.0661
-7.750 -0.3727 0.08820 0.08502 -0.0276 1.0000 0.0667
-7.500 -0.3771 0.08618 0.08305 -0.0276 0.9980 0.0680
-7.250 -0.3561 0.08003 0.07688 -0.0413 0.9883 0.0730
-7.000 -0.3347 0.06947 0.06619 -0.0608 0.9773 0.0758
-6.750 -0.3101 0.06799 0.06474 -0.0590 0.9740 0.0775
-6.500 -0.2797 0.06497 0.06167 -0.0630 0.9705 0.0811
-6.250 -0.2540 0.05479 0.05112 -0.0802 0.9584 0.0895
-6.000 -0.2226 0.05266 0.04904 -0.0817 0.9561 0.0914
-5.750 -0.2003 0.05047 0.04681 -0.0829 0.9473 0.0947
-5.500 -0.1652 0.04476 0.04078 -0.0911 0.9426 0.1052
-5.250 -0.1454 0.03144 0.02607 -0.0961 0.9317 0.0736
-5.000 -0.1116 0.02705 0.02129 -0.0990 0.9283 0.0704
-4.750 -0.0734 0.02417 0.01792 -0.1015 0.9257 0.0703
-4.500 -0.0482 0.02225 0.01564 -0.1010 0.9157 0.0701
-4.250 -0.0093 0.02039 0.01342 -0.1030 0.9115 0.0707
-4.000 0.0195 0.01919 0.01196 -0.1028 0.9021 0.0717
-3.750 0.0554 0.01828 0.01081 -0.1039 0.8964 0.0739
-3.500 0.0832 0.01712 0.00950 -0.1037 0.8877 0.0760
-3.250 0.1150 0.01605 0.00840 -0.1042 0.8811 0.0788
-3.000 0.1423 0.01543 0.00776 -0.1038 0.8719 0.0819
-2.750 0.1734 0.01483 0.00709 -0.1039 0.8647 0.0863
-2.500 0.1985 0.01420 0.00647 -0.1032 0.8547 0.0921
-2.250 0.2288 0.01369 0.00594 -0.1033 0.8477 0.0998
-2.000 0.2529 0.01325 0.00556 -0.1023 0.8370 0.1099
-1.750 0.2806 0.01287 0.00521 -0.1020 0.8287 0.1308
-1.500 0.3063 0.01241 0.00503 -0.1014 0.8192 0.1928
-1.250 0.3319 0.01214 0.00495 -0.1008 0.8099 0.2601
-1.000 0.3592 0.01190 0.00480 -0.1005 0.8015 0.3080
-0.750 0.3833 0.01165 0.00475 -0.0996 0.7912 0.3622
-0.500 0.4060 0.01102 0.00469 -0.0985 0.7832 0.5209
-0.250 0.4843 0.00989 0.00458 -0.1080 0.7746 1.0000
0.000 0.5090 0.00995 0.00448 -0.1070 0.7641 1.0000
0.250 0.5343 0.01000 0.00436 -0.1062 0.7535 1.0000
0.500 0.5575 0.01008 0.00433 -0.1050 0.7409 1.0000
0.750 0.5814 0.01015 0.00428 -0.1039 0.7287 1.0000
1.000 0.6059 0.01023 0.00424 -0.1029 0.7167 1.0000
1.250 0.6309 0.01031 0.00418 -0.1020 0.7048 1.0000
1.500 0.6547 0.01040 0.00418 -0.1009 0.6918 1.0000
1.750 0.6786 0.01051 0.00422 -0.0999 0.6792 1.0000
2.000 0.7032 0.01064 0.00426 -0.0990 0.6675 1.0000
2.250 0.7284 0.01078 0.00430 -0.0983 0.6564 1.0000
2.500 0.7529 0.01091 0.00437 -0.0974 0.6443 1.0000
2.750 0.7768 0.01105 0.00446 -0.0964 0.6313 1.0000
3.000 0.8010 0.01120 0.00456 -0.0955 0.6183 1.0000
3.250 0.8254 0.01136 0.00465 -0.0947 0.6056 1.0000
3.500 0.8498 0.01153 0.00476 -0.0938 0.5931 1.0000
3.750 0.8740 0.01170 0.00487 -0.0929 0.5802 1.0000
4.000 0.8976 0.01186 0.00501 -0.0920 0.5661 1.0000
4.250 0.9210 0.01203 0.00516 -0.0910 0.5516 1.0000
4.500 0.9444 0.01222 0.00531 -0.0900 0.5368 1.0000
4.750 0.9675 0.01241 0.00547 -0.0889 0.5217 1.0000
5.000 0.9904 0.01263 0.00566 -0.0879 0.5065 1.0000
5.250 1.0130 0.01288 0.00586 -0.0868 0.4907 1.0000
5.500 1.0352 0.01316 0.00609 -0.0856 0.4742 1.0000
5.750 1.0567 0.01348 0.00633 -0.0844 0.4569 1.0000
6.000 1.0777 0.01383 0.00664 -0.0830 0.4384 1.0000
6.250 1.0980 0.01420 0.00697 -0.0816 0.4186 1.0000
6.500 1.1180 0.01463 0.00733 -0.0802 0.3991 1.0000
6.750 1.1374 0.01509 0.00773 -0.0787 0.3802 1.0000
7.000 1.1564 0.01558 0.00813 -0.0771 0.3621 1.0000
7.250 1.1753 0.01602 0.00855 -0.0756 0.3442 1.0000
7.500 1.1943 0.01651 0.00898 -0.0741 0.3293 1.0000
7.750 1.2136 0.01702 0.00946 -0.0726 0.3170 1.0000
8.000 1.2326 0.01748 0.00993 -0.0712 0.3045 1.0000
8.250 1.2507 0.01796 0.01042 -0.0696 0.2923 1.0000
8.500 1.2682 0.01848 0.01092 -0.0680 0.2809 1.0000
8.750 1.2848 0.01905 0.01145 -0.0663 0.2702 1.0000
9.000 1.3011 0.01954 0.01198 -0.0644 0.2594 1.0000
9.250 1.3158 0.02005 0.01254 -0.0624 0.2489 1.0000
9.500 1.3278 0.02063 0.01310 -0.0599 0.2382 1.0000
9.750 1.3392 0.02121 0.01369 -0.0574 0.2277 1.0000
10.000 1.3523 0.02173 0.01434 -0.0553 0.2180 1.0000
10.250 1.3634 0.02240 0.01503 -0.0529 0.2086 1.0000
10.500 1.3737 0.02305 0.01574 -0.0506 0.1979 1.0000
10.750 1.3839 0.02372 0.01650 -0.0483 0.1847 1.0000
11.000 1.3914 0.02456 0.01737 -0.0459 0.1679 1.0000
11.250 1.3965 0.02566 0.01844 -0.0434 0.1356 1.0000
11.500 1.3851 0.02807 0.02047 -0.0398 0.0903 1.0000
11.750 1.3718 0.03096 0.02316 -0.0364 0.0646 1.0000
12.000 1.3646 0.03357 0.02572 -0.0339 0.0525 1.0000
12.250 1.3582 0.03624 0.02839 -0.0319 0.0471 1.0000
12.500 1.3569 0.03862 0.03088 -0.0305 0.0434 1.0000
12.750 1.3514 0.04149 0.03380 -0.0292 0.0408 1.0000
13.000 1.3449 0.04461 0.03700 -0.0282 0.0390 1.0000
13.250 1.3430 0.04741 0.03993 -0.0275 0.0373 1.0000
13.500 1.3398 0.05044 0.04307 -0.0270 0.0360 1.0000
13.750 1.3358 0.05367 0.04639 -0.0268 0.0349 1.0000
14.000 1.3301 0.05720 0.04999 -0.0266 0.0339 1.0000
14.250 1.3238 0.06083 0.05366 -0.0265 0.0331 1.0000
14.500 1.3224 0.06398 0.05688 -0.0263 0.0323 1.0000
14.750 1.3235 0.06694 0.05996 -0.0262 0.0316 1.0000
15.000 1.3245 0.06996 0.06310 -0.0263 0.0307 1.0000
15.250 1.3259 0.07296 0.06619 -0.0264 0.0298 1.0000
15.500 1.3263 0.07614 0.06943 -0.0268 0.0288 1.0000
15.750 1.3293 0.07894 0.07228 -0.0268 0.0281 1.0000
16.000 1.3360 0.08112 0.07444 -0.0262 0.0273 1.0000
16.250 1.3449 0.08316 0.07654 -0.0252 0.0267 1.0000
16.500 1.3464 0.08646 0.08002 -0.0257 0.0264 1.0000
16.750 1.3466 0.08999 0.08373 -0.0263 0.0261 1.0000
17.000 1.3456 0.09380 0.08772 -0.0272 0.0258 1.0000
17.250 1.3430 0.09790 0.09201 -0.0283 0.0256 1.0000
17.500 1.3381 0.10246 0.09677 -0.0298 0.0254 1.0000
17.750 1.3311 0.10744 0.10195 -0.0318 0.0252 1.0000
18.000 1.3223 0.11286 0.10758 -0.0343 0.0250 1.0000
18.250 1.3119 0.11868 0.11360 -0.0372 0.0248 1.0000
18.500 1.2994 0.12507 0.12019 -0.0406 0.0248 1.0000
18.750 1.2853 0.13196 0.12729 -0.0446 0.0248 1.0000
19.000 1.2689 0.13958 0.13512 -0.0494 0.0247 1.0000
19.250 1.2480 0.14856 0.14433 -0.0551 0.0250 1.0000
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Polar data table (+)
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