GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 50,000 Max Cl/Cd: 32.28 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe693-il-50000.txt Download as CSV file: xf-goe693-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3524 0.10902 0.10186 -0.0293 1.0000 0.2608
-8.500 -0.3438 0.10520 0.09807 -0.0284 1.0000 0.2670
-8.250 -0.3546 0.10391 0.09690 -0.0272 1.0000 0.2772
-8.000 -0.3430 0.10022 0.09324 -0.0257 1.0000 0.2864
-7.750 -0.3747 0.10041 0.09364 -0.0235 1.0000 0.2947
-7.500 -0.3563 0.09644 0.08966 -0.0217 1.0000 0.3080
-7.250 -0.3632 0.09426 0.08760 -0.0192 1.0000 0.3170
-7.000 -0.3897 0.09400 0.08751 -0.0151 1.0000 0.3268
-6.750 -0.3807 0.09083 0.08439 -0.0127 1.0000 0.3378
-6.500 -0.4320 0.09191 0.08572 -0.0074 1.0000 0.3444
-6.250 -0.4183 0.08860 0.08242 -0.0043 1.0000 0.3576
-6.000 -0.4268 0.08661 0.08053 -0.0009 1.0000 0.3686
-5.750 -0.4488 0.08537 0.07941 0.0025 1.0000 0.3813
-5.250 -0.4631 0.08159 0.07577 0.0095 1.0000 0.4149
-5.000 -0.4614 0.07958 0.07379 0.0136 1.0000 0.4378
-4.500 -0.4540 0.05895 0.05196 -0.0281 1.0000 0.2305
-4.250 -0.4255 0.05152 0.04373 -0.0341 1.0000 0.1981
-4.000 -0.4040 0.04820 0.04011 -0.0351 1.0000 0.1932
-3.750 -0.3808 0.04508 0.03657 -0.0364 1.0000 0.1922
-3.500 -0.3555 0.04241 0.03328 -0.0378 1.0000 0.1954
-3.250 -0.3317 0.04018 0.03071 -0.0384 1.0000 0.1990
-3.000 -0.3094 0.03869 0.02905 -0.0384 1.0000 0.2054
-2.750 -0.2840 0.03717 0.02706 -0.0390 1.0000 0.2150
-2.500 -0.2610 0.03607 0.02581 -0.0390 1.0000 0.2252
-2.250 -0.2378 0.03512 0.02472 -0.0391 1.0000 0.2387
-2.000 -0.2140 0.03430 0.02373 -0.0392 1.0000 0.2534
-1.750 -0.1904 0.03368 0.02300 -0.0392 1.0000 0.2707
-1.500 -0.1672 0.03321 0.02243 -0.0392 1.0000 0.2897
-1.250 -0.1439 0.03287 0.02199 -0.0392 1.0000 0.3103
-1.000 -0.1205 0.03262 0.02177 -0.0391 1.0000 0.3331
-0.750 -0.0954 0.03252 0.02164 -0.0394 1.0000 0.3611
-0.500 -0.0697 0.03237 0.02167 -0.0398 1.0000 0.3976
-0.250 -0.0417 0.03201 0.02183 -0.0405 1.0000 0.4680
0.000 -0.0234 0.03011 0.02157 -0.0379 0.9979 1.0000
0.250 0.0300 0.03154 0.02227 -0.0438 0.9854 1.0000
0.500 0.0799 0.03286 0.02320 -0.0491 0.9715 1.0000
0.750 0.1261 0.03403 0.02408 -0.0536 0.9569 1.0000
1.000 0.1675 0.03506 0.02489 -0.0571 0.9423 1.0000
1.250 0.2050 0.03600 0.02566 -0.0599 0.9278 1.0000
1.500 0.2399 0.03691 0.02644 -0.0621 0.9138 1.0000
1.750 0.2741 0.03782 0.02724 -0.0642 0.8998 1.0000
2.000 0.3081 0.03872 0.02805 -0.0661 0.8856 1.0000
2.250 0.3418 0.03961 0.02887 -0.0679 0.8713 1.0000
2.500 0.3752 0.04048 0.02970 -0.0696 0.8569 1.0000
2.750 0.4084 0.04133 0.03051 -0.0711 0.8421 1.0000
3.000 0.4412 0.04217 0.03133 -0.0725 0.8272 1.0000
3.250 0.4736 0.04299 0.03215 -0.0737 0.8122 1.0000
3.500 0.5062 0.04379 0.03295 -0.0749 0.7973 1.0000
3.750 0.5415 0.04451 0.03370 -0.0763 0.7831 1.0000
4.000 0.5733 0.04524 0.03447 -0.0771 0.7683 1.0000
4.250 0.5977 0.04618 0.03544 -0.0770 0.7530 1.0000
4.500 0.6202 0.04721 0.03651 -0.0767 0.7378 1.0000
4.750 0.6447 0.04811 0.03747 -0.0764 0.7223 1.0000
5.000 0.6706 0.04884 0.03826 -0.0761 0.7067 1.0000
5.250 0.6975 0.04943 0.03891 -0.0757 0.6910 1.0000
5.500 0.7292 0.04954 0.03911 -0.0754 0.6749 1.0000
5.750 0.7647 0.04914 0.03881 -0.0749 0.6586 1.0000
6.000 0.7973 0.04882 0.03860 -0.0741 0.6429 1.0000
6.250 0.8238 0.04896 0.03884 -0.0731 0.6278 1.0000
6.500 0.8458 0.04950 0.03948 -0.0718 0.6130 1.0000
6.750 0.8681 0.04999 0.04010 -0.0705 0.5985 1.0000
7.000 0.8916 0.05036 0.04060 -0.0692 0.5842 1.0000
7.250 0.9235 0.04984 0.04023 -0.0680 0.5699 1.0000
7.500 0.9658 0.04829 0.03889 -0.0672 0.5551 1.0000
7.750 1.0104 0.04650 0.03728 -0.0664 0.5389 1.0000
8.000 1.0577 0.04451 0.03547 -0.0659 0.5216 1.0000
8.250 1.1402 0.03946 0.03051 -0.0675 0.4993 1.0000
8.500 1.1616 0.03925 0.03036 -0.0651 0.4740 1.0000
8.750 1.1964 0.03840 0.02949 -0.0639 0.4482 1.0000
9.000 1.2314 0.03815 0.02915 -0.0633 0.4241 1.0000
9.250 1.2499 0.03919 0.03024 -0.0615 0.4029 1.0000
9.500 1.2682 0.04033 0.03145 -0.0597 0.3825 1.0000
9.750 1.2939 0.04132 0.03242 -0.0588 0.3628 1.0000
10.000 1.3167 0.04256 0.03365 -0.0576 0.3432 1.0000
10.250 1.3249 0.04424 0.03549 -0.0548 0.3245 1.0000
10.500 1.3359 0.04511 0.03638 -0.0521 0.3022 1.0000
10.750 1.3452 0.04540 0.03655 -0.0490 0.2783 1.0000
11.000 1.3449 0.04626 0.03745 -0.0450 0.2582 1.0000
11.250 1.3549 0.04664 0.03759 -0.0422 0.2362 1.0000
11.500 1.3483 0.04819 0.03924 -0.0379 0.2190 1.0000
11.750 1.3419 0.04980 0.04084 -0.0336 0.2012 1.0000
12.000 1.3478 0.05175 0.04242 -0.0309 0.1771 1.0000
12.250 1.3427 0.05476 0.04549 -0.0276 0.1603 1.0000
12.500 1.3425 0.05795 0.04870 -0.0251 0.1461 1.0000
12.750 1.3485 0.06084 0.05154 -0.0232 0.1341 1.0000
13.000 1.3270 0.06451 0.05565 -0.0198 0.1306 1.0000
13.250 1.3254 0.06760 0.05886 -0.0180 0.1239 1.0000
13.500 1.3193 0.07148 0.06290 -0.0163 0.1198 1.0000
13.750 1.2938 0.07635 0.06813 -0.0147 0.1188 1.0000
14.000 1.2657 0.08192 0.07401 -0.0141 0.1184 1.0000
14.250 1.2342 0.08839 0.08076 -0.0146 0.1187 1.0000
14.500 1.1999 0.09591 0.08850 -0.0163 0.1195 1.0000
14.750 1.1650 0.10443 0.09720 -0.0193 0.1206 1.0000
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Polar data table (+)
Polar graphs
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