GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 500,000 Max Cl/Cd: 79.34 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe681-il-500000.txt Download as CSV file: xf-goe681-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 681 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5738 0.07986 0.07676 -0.0756 1.0000 0.0373
-14.000 -0.6558 0.06382 0.06046 -0.0869 1.0000 0.0368
-13.750 -0.7042 0.05441 0.05084 -0.0937 1.0000 0.0366
-13.500 -0.7410 0.04833 0.04458 -0.0970 1.0000 0.0365
-13.250 -0.7735 0.04475 0.04089 -0.0965 1.0000 0.0364
-13.000 -0.7801 0.04055 0.03645 -0.1009 0.9963 0.0364
-12.750 -0.7730 0.03718 0.03283 -0.1046 0.9900 0.0364
-12.500 -0.7603 0.03459 0.03003 -0.1067 0.9834 0.0365
-12.250 -0.7470 0.03248 0.02771 -0.1075 0.9755 0.0366
-12.000 -0.7249 0.03042 0.02546 -0.1091 0.9701 0.0367
-11.750 -0.7037 0.02876 0.02363 -0.1098 0.9632 0.0369
-11.500 -0.6784 0.02722 0.02192 -0.1110 0.9572 0.0371
-11.250 -0.6460 0.02577 0.02030 -0.1133 0.9538 0.0373
-11.000 -0.6212 0.02467 0.01905 -0.1138 0.9438 0.0374
-10.750 -0.5872 0.02354 0.01778 -0.1159 0.9382 0.0376
-10.500 -0.5614 0.02210 0.01625 -0.1164 0.9272 0.0379
-10.250 -0.5313 0.02083 0.01492 -0.1176 0.9181 0.0382
-10.000 -0.5054 0.01994 0.01397 -0.1177 0.9062 0.0385
-9.750 -0.4822 0.01923 0.01320 -0.1172 0.8941 0.0389
-9.500 -0.4579 0.01862 0.01251 -0.1169 0.8834 0.0393
-9.250 -0.4377 0.01809 0.01192 -0.1156 0.8716 0.0398
-9.000 -0.4159 0.01758 0.01132 -0.1145 0.8616 0.0402
-8.750 -0.3953 0.01709 0.01074 -0.1133 0.8514 0.0405
-8.500 -0.3736 0.01663 0.01020 -0.1121 0.8427 0.0409
-8.250 -0.3529 0.01619 0.00969 -0.1108 0.8335 0.0413
-8.000 -0.3301 0.01580 0.00919 -0.1098 0.8254 0.0416
-7.750 -0.3091 0.01542 0.00877 -0.1084 0.8171 0.0420
-7.500 -0.2876 0.01496 0.00823 -0.1072 0.8094 0.0424
-7.250 -0.2674 0.01445 0.00771 -0.1058 0.8019 0.0431
-7.000 -0.2459 0.01406 0.00729 -0.1045 0.7940 0.0437
-6.750 -0.2223 0.01375 0.00691 -0.1036 0.7871 0.0444
-6.500 -0.1997 0.01344 0.00659 -0.1025 0.7802 0.0452
-6.250 -0.1762 0.01316 0.00625 -0.1015 0.7729 0.0461
-5.750 -0.1292 0.01256 0.00558 -0.0995 0.7590 0.0487
-5.500 -0.1050 0.01232 0.00530 -0.0986 0.7513 0.0505
-5.000 -0.0570 0.01182 0.00476 -0.0967 0.7349 0.0559
-4.750 -0.0323 0.01158 0.00450 -0.0959 0.7272 0.0623
-4.500 -0.0091 0.01126 0.00426 -0.0948 0.7188 0.0783
-4.250 0.0140 0.01091 0.00399 -0.0937 0.7104 0.1019
-4.000 0.0375 0.01064 0.00381 -0.0928 0.7023 0.1283
-3.750 0.0622 0.01046 0.00373 -0.0920 0.6945 0.1541
-3.500 0.0883 0.01042 0.00368 -0.0914 0.6874 0.1729
-3.250 0.1144 0.01037 0.00366 -0.0908 0.6799 0.1859
-3.000 0.1401 0.01033 0.00361 -0.0902 0.6722 0.1970
-2.750 0.1667 0.01034 0.00357 -0.0897 0.6650 0.2047
-2.500 0.1919 0.01026 0.00352 -0.0890 0.6569 0.2136
-2.000 0.2436 0.01022 0.00341 -0.0877 0.6414 0.2268
-1.750 0.2689 0.01018 0.00336 -0.0869 0.6334 0.2340
-1.500 0.2949 0.01019 0.00333 -0.0863 0.6256 0.2401
-1.250 0.3198 0.01012 0.00326 -0.0855 0.6171 0.2471
-1.000 0.3448 0.01011 0.00322 -0.0848 0.6096 0.2546
-0.750 0.3705 0.01010 0.00320 -0.0841 0.6011 0.2612
-0.500 0.3945 0.01005 0.00315 -0.0832 0.5927 0.2711
-0.250 0.4194 0.01002 0.00313 -0.0824 0.5833 0.2801
0.500 0.4901 0.00992 0.00307 -0.0793 0.5542 0.3231
0.750 0.5126 0.00978 0.00307 -0.0781 0.5437 0.3599
1.000 0.5322 0.00958 0.00311 -0.0764 0.5331 0.4402
1.250 0.5495 0.00931 0.00314 -0.0743 0.5212 0.5467
1.500 0.5613 0.00890 0.00322 -0.0708 0.5096 0.6994
1.750 0.5775 0.00865 0.00339 -0.0679 0.4957 0.8481
2.000 0.6375 0.00891 0.00368 -0.0744 0.4728 0.9327
2.250 0.6921 0.00929 0.00391 -0.0799 0.4476 0.9569
2.500 0.7295 0.00966 0.00413 -0.0819 0.4241 0.9718
2.750 0.7662 0.01004 0.00435 -0.0838 0.4003 0.9826
3.000 0.8058 0.01044 0.00459 -0.0864 0.3789 0.9903
3.250 0.8463 0.01081 0.00482 -0.0892 0.3616 0.9966
3.500 0.8823 0.01112 0.00502 -0.0911 0.3483 1.0000
3.750 0.8930 0.01137 0.00518 -0.0878 0.3391 1.0000
4.000 0.9062 0.01155 0.00532 -0.0850 0.3319 1.0000
4.250 0.9182 0.01177 0.00548 -0.0819 0.3248 1.0000
4.500 0.9290 0.01203 0.00567 -0.0786 0.3186 1.0000
4.750 0.9418 0.01218 0.00582 -0.0756 0.3136 1.0000
5.000 0.9515 0.01238 0.00598 -0.0720 0.3086 1.0000
5.250 0.9606 0.01265 0.00619 -0.0683 0.3037 1.0000
5.500 0.9743 0.01287 0.00640 -0.0656 0.2996 1.0000
5.750 0.9901 0.01307 0.00660 -0.0633 0.2957 1.0000
6.000 1.0048 0.01333 0.00684 -0.0609 0.2915 1.0000
6.250 1.0187 0.01367 0.00712 -0.0584 0.2876 1.0000
6.500 1.0334 0.01402 0.00745 -0.0561 0.2837 1.0000
6.750 1.0518 0.01425 0.00769 -0.0545 0.2806 1.0000
7.000 1.0693 0.01452 0.00797 -0.0527 0.2772 1.0000
7.250 1.0859 0.01486 0.00829 -0.0509 0.2739 1.0000
7.500 1.1014 0.01526 0.00867 -0.0489 0.2707 1.0000
7.750 1.1170 0.01574 0.00911 -0.0471 0.2674 1.0000
8.000 1.1359 0.01603 0.00944 -0.0458 0.2653 1.0000
8.250 1.1543 0.01637 0.00980 -0.0444 0.2629 1.0000
8.500 1.1724 0.01673 0.01018 -0.0430 0.2603 1.0000
8.750 1.1893 0.01715 0.01060 -0.0416 0.2575 1.0000
9.000 1.2056 0.01764 0.01106 -0.0401 0.2546 1.0000
9.250 1.2215 0.01823 0.01161 -0.0386 0.2511 1.0000
9.500 1.2399 0.01862 0.01205 -0.0375 0.2494 1.0000
9.750 1.2577 0.01904 0.01252 -0.0363 0.2467 1.0000
10.000 1.2752 0.01951 0.01302 -0.0352 0.2445 1.0000
10.250 1.2922 0.02002 0.01355 -0.0340 0.2421 1.0000
10.500 1.3081 0.02061 0.01413 -0.0328 0.2396 1.0000
10.750 1.3242 0.02125 0.01475 -0.0316 0.2373 1.0000
11.000 1.3410 0.02186 0.01538 -0.0306 0.2348 1.0000
11.250 1.3577 0.02242 0.01601 -0.0296 0.2330 1.0000
11.500 1.3740 0.02302 0.01667 -0.0286 0.2306 1.0000
11.750 1.3894 0.02368 0.01736 -0.0276 0.2278 1.0000
12.000 1.4047 0.02439 0.01809 -0.0266 0.2256 1.0000
12.250 1.4183 0.02520 0.01889 -0.0255 0.2229 1.0000
12.500 1.4332 0.02598 0.01965 -0.0245 0.2202 1.0000
12.750 1.4479 0.02675 0.02051 -0.0237 0.2184 1.0000
13.000 1.4624 0.02755 0.02139 -0.0229 0.2161 1.0000
13.250 1.4762 0.02841 0.02231 -0.0220 0.2136 1.0000
13.500 1.4893 0.02934 0.02327 -0.0212 0.2111 1.0000
13.750 1.5004 0.03042 0.02435 -0.0203 0.2082 1.0000
14.000 1.5117 0.03149 0.02543 -0.0193 0.2053 1.0000
14.250 1.5247 0.03251 0.02656 -0.0187 0.2032 1.0000
14.500 1.5372 0.03359 0.02772 -0.0181 0.2005 1.0000
14.750 1.5484 0.03478 0.02895 -0.0174 0.1977 1.0000
15.000 1.5580 0.03610 0.03030 -0.0167 0.1950 1.0000
15.250 1.5651 0.03762 0.03181 -0.0159 0.1919 1.0000
15.500 1.5769 0.03886 0.03317 -0.0155 0.1893 1.0000
15.750 1.5872 0.04025 0.03465 -0.0151 0.1862 1.0000
16.000 1.5955 0.04183 0.03627 -0.0146 0.1827 1.0000
16.250 1.5996 0.04379 0.03824 -0.0141 0.1792 1.0000
16.500 1.6082 0.04539 0.03993 -0.0138 0.1758 1.0000
16.750 1.6155 0.04717 0.04179 -0.0135 0.1715 1.0000
17.000 1.6155 0.04970 0.04433 -0.0132 0.1663 1.0000
17.250 1.6213 0.05168 0.04639 -0.0130 0.1606 1.0000
17.500 1.6171 0.05473 0.04945 -0.0128 0.1535 1.0000
17.750 1.6172 0.05738 0.05215 -0.0128 0.1457 1.0000
18.000 1.6070 0.06121 0.05598 -0.0128 0.1354 1.0000
18.250 1.5922 0.06564 0.06041 -0.0130 0.1246 1.0000
18.500 1.5707 0.07098 0.06575 -0.0135 0.1135 1.0000
18.750 1.5447 0.07705 0.07183 -0.0143 0.1030 1.0000
19.000 1.5178 0.08338 0.07820 -0.0154 0.0941 1.0000
19.250 1.4899 0.09009 0.08496 -0.0168 0.0871 1.0000
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Polar data table (+)
Polar graphs
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