GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.08 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe677-il-1000000-n5.txt Download as CSV file: xf-goe677-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.3325 0.05191 0.04914 -0.0459 1.0000 0.0090
-17.000 -1.3640 0.04494 0.04193 -0.0490 1.0000 0.0090
-16.750 -1.3819 0.04078 0.03758 -0.0489 1.0000 0.0091
-16.500 -1.3929 0.03772 0.03437 -0.0476 1.0000 0.0093
-16.250 -1.3991 0.03530 0.03180 -0.0456 1.0000 0.0095
-16.000 -1.4016 0.03331 0.02967 -0.0434 1.0000 0.0098
-15.750 -1.4008 0.03164 0.02787 -0.0409 1.0000 0.0100
-15.500 -1.3977 0.03020 0.02630 -0.0384 1.0000 0.0103
-15.250 -1.3945 0.02875 0.02474 -0.0356 1.0000 0.0108
-15.000 -1.3886 0.02747 0.02337 -0.0330 1.0000 0.0113
-14.750 -1.3775 0.02632 0.02212 -0.0311 1.0000 0.0119
-14.500 -1.3638 0.02530 0.02101 -0.0295 1.0000 0.0125
-14.250 -1.3483 0.02438 0.01999 -0.0280 1.0000 0.0130
-14.000 -1.3316 0.02350 0.01904 -0.0267 1.0000 0.0137
-13.750 -1.3133 0.02273 0.01822 -0.0255 1.0000 0.0146
-13.500 -1.2939 0.02205 0.01749 -0.0245 1.0000 0.0154
-13.250 -1.2740 0.02140 0.01677 -0.0235 1.0000 0.0161
-13.000 -1.2535 0.02078 0.01607 -0.0225 1.0000 0.0167
-12.750 -1.2323 0.02020 0.01544 -0.0217 1.0000 0.0174
-12.500 -1.2098 0.01975 0.01496 -0.0210 1.0000 0.0181
-12.250 -1.1869 0.01933 0.01451 -0.0203 1.0000 0.0189
-12.000 -1.1639 0.01891 0.01405 -0.0196 1.0000 0.0196
-11.750 -1.1408 0.01848 0.01356 -0.0190 1.0000 0.0202
-11.500 -1.1175 0.01805 0.01307 -0.0183 1.0000 0.0206
-11.250 -1.0940 0.01765 0.01259 -0.0177 1.0000 0.0210
-11.000 -1.0711 0.01715 0.01204 -0.0170 1.0000 0.0214
-10.750 -1.0479 0.01669 0.01155 -0.0163 1.0000 0.0221
-10.500 -1.0230 0.01634 0.01119 -0.0159 0.9979 0.0226
-10.250 -0.9916 0.01600 0.01082 -0.0169 0.9786 0.0233
-9.750 -0.9364 0.01542 0.01004 -0.0170 0.9092 0.0243
-9.500 -0.9130 0.01519 0.00968 -0.0161 0.8829 0.0248
-9.250 -0.8887 0.01495 0.00932 -0.0154 0.8579 0.0253
-9.000 -0.8640 0.01474 0.00897 -0.0148 0.8296 0.0257
-8.750 -0.8389 0.01458 0.00865 -0.0142 0.7969 0.0260
-8.500 -0.8140 0.01433 0.00825 -0.0137 0.7671 0.0264
-8.250 -0.7900 0.01386 0.00766 -0.0131 0.7448 0.0271
-8.000 -0.7647 0.01353 0.00723 -0.0127 0.7286 0.0276
-7.750 -0.7389 0.01324 0.00686 -0.0123 0.7156 0.0281
-7.500 -0.7127 0.01299 0.00655 -0.0120 0.7036 0.0286
-7.250 -0.6864 0.01276 0.00624 -0.0118 0.6923 0.0291
-7.000 -0.6600 0.01250 0.00591 -0.0115 0.6824 0.0295
-6.750 -0.6335 0.01225 0.00560 -0.0113 0.6749 0.0299
-6.500 -0.6068 0.01200 0.00530 -0.0110 0.6685 0.0304
-6.250 -0.5801 0.01178 0.00501 -0.0108 0.6622 0.0308
-6.000 -0.5531 0.01155 0.00474 -0.0106 0.6565 0.0313
-5.750 -0.5261 0.01135 0.00449 -0.0105 0.6509 0.0316
-5.500 -0.4989 0.01116 0.00425 -0.0103 0.6463 0.0320
-5.250 -0.4716 0.01096 0.00402 -0.0102 0.6427 0.0323
-5.000 -0.4447 0.01069 0.00372 -0.0100 0.6383 0.0335
-4.750 -0.4175 0.01050 0.00351 -0.0099 0.6338 0.0346
-4.250 -0.3625 0.01017 0.00314 -0.0097 0.6265 0.0365
-4.000 -0.3347 0.01001 0.00298 -0.0096 0.6225 0.0375
-3.750 -0.3070 0.00988 0.00282 -0.0096 0.6185 0.0385
-3.500 -0.2792 0.00977 0.00267 -0.0095 0.6144 0.0394
-3.250 -0.2515 0.00960 0.00251 -0.0095 0.6106 0.0417
-3.000 -0.2236 0.00947 0.00239 -0.0095 0.6070 0.0442
-2.750 -0.1956 0.00935 0.00228 -0.0095 0.6035 0.0465
-2.500 -0.1675 0.00926 0.00217 -0.0095 0.6002 0.0482
-2.250 -0.1396 0.00915 0.00206 -0.0095 0.5969 0.0522
-2.000 -0.1114 0.00903 0.00198 -0.0095 0.5938 0.0561
-1.750 -0.0831 0.00895 0.00190 -0.0096 0.5898 0.0588
-1.500 -0.0551 0.00885 0.00181 -0.0096 0.5852 0.0637
-1.250 -0.0270 0.00877 0.00173 -0.0096 0.5809 0.0682
-1.000 0.0015 0.00869 0.00166 -0.0097 0.5769 0.0714
-0.750 0.0297 0.00860 0.00160 -0.0098 0.5720 0.0778
-0.500 0.0578 0.00853 0.00154 -0.0098 0.5664 0.0848
-0.250 0.0857 0.00839 0.00149 -0.0098 0.5604 0.1080
0.000 0.1133 0.00827 0.00145 -0.0098 0.5511 0.1418
0.250 0.1410 0.00818 0.00139 -0.0098 0.5367 0.1631
0.500 0.1669 0.00788 0.00134 -0.0096 0.5200 0.2582
0.750 0.1933 0.00770 0.00131 -0.0094 0.4999 0.3256
1.000 0.2162 0.00722 0.00126 -0.0087 0.4758 0.4950
1.250 0.2311 0.00622 0.00120 -0.0063 0.4559 0.7870
1.500 0.2545 0.00616 0.00133 -0.0051 0.4377 0.8698
1.750 0.2804 0.00626 0.00145 -0.0046 0.4247 0.9006
2.000 0.3077 0.00637 0.00152 -0.0044 0.4139 0.9126
2.250 0.3348 0.00648 0.00161 -0.0041 0.4031 0.9229
2.500 0.3618 0.00661 0.00170 -0.0038 0.3921 0.9321
2.750 0.3890 0.00674 0.00179 -0.0037 0.3798 0.9380
3.000 0.4158 0.00684 0.00187 -0.0034 0.3711 0.9453
3.250 0.4435 0.00695 0.00196 -0.0033 0.3643 0.9499
3.500 0.4708 0.00704 0.00204 -0.0031 0.3572 0.9547
3.750 0.4975 0.00716 0.00213 -0.0029 0.3486 0.9594
4.000 0.5260 0.00730 0.00222 -0.0031 0.3349 0.9619
4.250 0.5541 0.00745 0.00232 -0.0032 0.3205 0.9644
4.500 0.5816 0.00765 0.00244 -0.0032 0.3014 0.9675
4.750 0.6076 0.00791 0.00259 -0.0030 0.2746 0.9705
5.000 0.6333 0.00828 0.00279 -0.0029 0.2383 0.9725
5.250 0.6606 0.00867 0.00303 -0.0031 0.2051 0.9737
5.500 0.6882 0.00902 0.00326 -0.0034 0.1793 0.9751
5.750 0.7156 0.00938 0.00351 -0.0036 0.1566 0.9765
6.000 0.7414 0.00991 0.00384 -0.0037 0.1161 0.9784
6.250 0.7674 0.01036 0.00416 -0.0037 0.0917 0.9806
6.500 0.7941 0.01060 0.00438 -0.0037 0.0859 0.9827
6.750 0.8221 0.01084 0.00461 -0.0040 0.0821 0.9841
7.000 0.8513 0.01112 0.00487 -0.0046 0.0773 0.9850
7.250 0.8808 0.01135 0.00510 -0.0053 0.0746 0.9859
7.500 0.9105 0.01155 0.00533 -0.0060 0.0733 0.9868
7.750 0.9398 0.01178 0.00557 -0.0066 0.0706 0.9878
8.000 0.9685 0.01207 0.00585 -0.0072 0.0669 0.9889
8.250 0.9967 0.01238 0.00615 -0.0077 0.0625 0.9901
8.500 1.0249 0.01264 0.00641 -0.0082 0.0577 0.9915
8.750 1.0501 0.01316 0.00681 -0.0083 0.0421 0.9933
9.000 1.0728 0.01414 0.00761 -0.0083 0.0175 0.9947
9.250 1.0997 0.01463 0.00810 -0.0087 0.0146 0.9956
9.500 1.1268 0.01504 0.00855 -0.0091 0.0134 0.9968
9.750 1.1530 0.01551 0.00903 -0.0094 0.0124 0.9980
10.000 1.1783 0.01604 0.00958 -0.0096 0.0114 0.9994
10.250 1.1977 0.01650 0.01008 -0.0086 0.0107 1.0000
10.500 1.2112 0.01688 0.01050 -0.0062 0.0103 1.0000
10.750 1.2247 0.01730 0.01095 -0.0039 0.0099 1.0000
11.000 1.2381 0.01777 0.01145 -0.0017 0.0094 1.0000
11.250 1.2518 0.01829 0.01200 0.0003 0.0091 1.0000
11.500 1.2631 0.01887 0.01262 0.0027 0.0087 1.0000
11.750 1.2724 0.01957 0.01336 0.0052 0.0083 1.0000
12.000 1.2830 0.02034 0.01418 0.0073 0.0081 1.0000
12.250 1.2954 0.02110 0.01500 0.0088 0.0079 1.0000
12.500 1.3076 0.02198 0.01593 0.0101 0.0077 1.0000
12.750 1.3194 0.02295 0.01696 0.0113 0.0075 1.0000
13.000 1.3308 0.02403 0.01810 0.0122 0.0073 1.0000
13.250 1.3418 0.02521 0.01934 0.0131 0.0071 1.0000
13.500 1.3522 0.02651 0.02070 0.0137 0.0068 1.0000
13.750 1.3617 0.02796 0.02221 0.0143 0.0066 1.0000
14.000 1.3701 0.02959 0.02389 0.0147 0.0065 1.0000
14.250 1.3771 0.03140 0.02577 0.0151 0.0063 1.0000
14.500 1.3817 0.03350 0.02794 0.0153 0.0061 1.0000
14.750 1.3850 0.03579 0.03031 0.0155 0.0059 1.0000
15.000 1.3902 0.03790 0.03250 0.0156 0.0059 1.0000
15.250 1.3942 0.04015 0.03483 0.0156 0.0058 1.0000
15.500 1.3967 0.04260 0.03736 0.0155 0.0057 1.0000
15.750 1.3981 0.04519 0.04004 0.0154 0.0057 1.0000
16.000 1.3978 0.04797 0.04291 0.0152 0.0056 1.0000
16.250 1.3968 0.05092 0.04595 0.0149 0.0055 1.0000
16.500 1.3946 0.05410 0.04922 0.0144 0.0054 1.0000
16.750 1.3918 0.05747 0.05268 0.0138 0.0054 1.0000
17.000 1.3878 0.06112 0.05642 0.0129 0.0053 1.0000
17.250 1.3832 0.06498 0.06039 0.0118 0.0052 1.0000
17.500 1.3776 0.06905 0.06455 0.0107 0.0052 1.0000
17.750 1.3707 0.07344 0.06904 0.0092 0.0051 1.0000
18.000 1.3631 0.07801 0.07371 0.0077 0.0051 1.0000
18.250 1.3542 0.08278 0.07858 0.0060 0.0050 1.0000
18.500 1.3442 0.08780 0.08370 0.0042 0.0050 1.0000
18.750 1.3330 0.09309 0.08909 0.0022 0.0049 1.0000
19.000 1.3201 0.09872 0.09483 0.0000 0.0049 1.0000
19.250 1.3072 0.10441 0.10062 -0.0023 0.0049 1.0000
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Polar data table (+)
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