GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.61 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe676-il-1000000.txt Download as CSV file: xf-goe676-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.2297 0.05938 0.05679 -0.0412 1.0000 0.0132
-16.500 -1.2669 0.04836 0.04548 -0.0502 1.0000 0.0131
-16.250 -1.2862 0.04255 0.03949 -0.0534 1.0000 0.0132
-16.000 -1.2965 0.03879 0.03559 -0.0543 1.0000 0.0133
-15.750 -1.3000 0.03617 0.03285 -0.0540 1.0000 0.0135
-15.500 -1.2985 0.03421 0.03081 -0.0531 1.0000 0.0138
-15.250 -1.2941 0.03262 0.02913 -0.0519 1.0000 0.0140
-15.000 -1.2874 0.03130 0.02772 -0.0505 1.0000 0.0143
-14.750 -1.2797 0.03010 0.02643 -0.0489 1.0000 0.0146
-14.500 -1.2705 0.02905 0.02528 -0.0472 1.0000 0.0149
-14.250 -1.2600 0.02811 0.02424 -0.0453 1.0000 0.0153
-14.000 -1.2474 0.02728 0.02330 -0.0436 1.0000 0.0155
-13.750 -1.2368 0.02604 0.02193 -0.0419 1.0000 0.0159
-13.500 -1.2252 0.02482 0.02063 -0.0403 1.0000 0.0164
-13.250 -1.2065 0.02418 0.01996 -0.0393 1.0000 0.0169
-13.000 -1.1861 0.02367 0.01942 -0.0385 1.0000 0.0173
-12.750 -1.1654 0.02315 0.01884 -0.0377 1.0000 0.0178
-12.500 -1.1448 0.02259 0.01821 -0.0369 1.0000 0.0183
-12.250 -1.1237 0.02203 0.01757 -0.0362 1.0000 0.0187
-12.000 -1.1015 0.02157 0.01702 -0.0355 1.0000 0.0191
-11.750 -1.0852 0.02042 0.01575 -0.0342 1.0000 0.0197
-11.500 -1.0638 0.01989 0.01521 -0.0334 1.0000 0.0203
-11.250 -1.0405 0.01961 0.01491 -0.0328 1.0000 0.0209
-11.000 -1.0175 0.01931 0.01459 -0.0322 1.0000 0.0215
-10.750 -0.9953 0.01893 0.01416 -0.0314 1.0000 0.0221
-10.500 -0.9740 0.01853 0.01369 -0.0303 1.0000 0.0226
-10.250 -0.9536 0.01821 0.01330 -0.0291 1.0000 0.0230
-10.000 -0.9337 0.01800 0.01304 -0.0276 1.0000 0.0233
-9.750 -0.9219 0.01676 0.01171 -0.0251 0.9998 0.0243
-9.500 -0.8890 0.01638 0.01133 -0.0266 0.9978 0.0251
-9.250 -0.8556 0.01605 0.01098 -0.0280 0.9958 0.0258
-9.000 -0.8222 0.01564 0.01052 -0.0295 0.9941 0.0266
-8.750 -0.7899 0.01524 0.01006 -0.0307 0.9914 0.0273
-8.500 -0.7572 0.01498 0.00976 -0.0319 0.9876 0.0279
-8.250 -0.7266 0.01413 0.00881 -0.0328 0.9838 0.0287
-8.000 -0.6992 0.01346 0.00811 -0.0330 0.9769 0.0297
-7.750 -0.6700 0.01313 0.00777 -0.0335 0.9706 0.0305
-7.500 -0.6444 0.01286 0.00748 -0.0330 0.9613 0.0313
-7.250 -0.6195 0.01255 0.00712 -0.0324 0.9520 0.0321
-7.000 -0.5954 0.01225 0.00676 -0.0315 0.9417 0.0328
-6.750 -0.5702 0.01202 0.00648 -0.0309 0.9311 0.0334
-6.500 -0.5447 0.01182 0.00623 -0.0304 0.9209 0.0338
-6.250 -0.5222 0.01111 0.00542 -0.0293 0.9097 0.0350
-6.000 -0.4970 0.01075 0.00503 -0.0288 0.8985 0.0361
-5.750 -0.4710 0.01052 0.00476 -0.0284 0.8882 0.0372
-5.250 -0.4181 0.01010 0.00424 -0.0277 0.8674 0.0393
-5.000 -0.3913 0.00992 0.00400 -0.0274 0.8576 0.0402
-4.750 -0.3649 0.00968 0.00368 -0.0271 0.8473 0.0413
-4.500 -0.3385 0.00937 0.00335 -0.0267 0.8371 0.0436
-4.250 -0.3114 0.00922 0.00317 -0.0265 0.8271 0.0457
-4.000 -0.2839 0.00910 0.00300 -0.0264 0.8166 0.0478
-3.750 -0.2566 0.00892 0.00277 -0.0262 0.8058 0.0504
-3.500 -0.2295 0.00874 0.00259 -0.0260 0.7949 0.0547
-3.250 -0.2017 0.00866 0.00246 -0.0260 0.7836 0.0580
-3.000 -0.1742 0.00846 0.00228 -0.0259 0.7726 0.0641
-2.750 -0.1464 0.00837 0.00215 -0.0258 0.7611 0.0688
-2.500 -0.1188 0.00823 0.00199 -0.0257 0.7484 0.0757
-2.250 -0.0911 0.00813 0.00186 -0.0257 0.7343 0.0821
-2.000 -0.0635 0.00799 0.00174 -0.0256 0.7192 0.0941
-1.750 -0.0365 0.00779 0.00164 -0.0255 0.7034 0.1316
-1.500 -0.0090 0.00768 0.00156 -0.0254 0.6883 0.1593
-1.250 0.0181 0.00752 0.00147 -0.0254 0.6740 0.1933
-1.000 0.0432 0.00704 0.00136 -0.0251 0.6614 0.3137
-0.750 0.0677 0.00652 0.00128 -0.0247 0.6508 0.4590
-0.500 0.0911 0.00598 0.00121 -0.0240 0.6400 0.6067
-0.250 0.1141 0.00552 0.00119 -0.0230 0.6285 0.7452
0.000 0.1387 0.00535 0.00126 -0.0221 0.6180 0.8254
0.250 0.1648 0.00535 0.00132 -0.0215 0.6088 0.8653
0.500 0.1918 0.00537 0.00137 -0.0211 0.6001 0.8884
0.750 0.2185 0.00544 0.00142 -0.0207 0.5899 0.9056
1.000 0.2451 0.00549 0.00147 -0.0202 0.5795 0.9187
1.250 0.2720 0.00555 0.00152 -0.0198 0.5702 0.9286
1.500 0.2984 0.00564 0.00156 -0.0193 0.5602 0.9384
1.750 0.3252 0.00570 0.00162 -0.0189 0.5491 0.9460
2.000 0.3511 0.00579 0.00166 -0.0183 0.5360 0.9543
2.250 0.3779 0.00591 0.00174 -0.0179 0.5200 0.9624
2.500 0.4044 0.00603 0.00181 -0.0174 0.5034 0.9702
2.750 0.4359 0.00617 0.00188 -0.0182 0.4849 0.9735
3.000 0.4677 0.00634 0.00196 -0.0191 0.4637 0.9768
3.250 0.4982 0.00651 0.00205 -0.0197 0.4442 0.9806
3.500 0.5320 0.00670 0.00216 -0.0211 0.4249 0.9836
3.750 0.5711 0.00691 0.00229 -0.0237 0.4070 0.9849
4.000 0.6073 0.00709 0.00241 -0.0257 0.3910 0.9863
4.250 0.6405 0.00726 0.00252 -0.0270 0.3754 0.9877
4.500 0.6729 0.00743 0.00263 -0.0282 0.3597 0.9893
5.000 0.7354 0.00783 0.00289 -0.0301 0.3243 0.9930
5.250 0.7676 0.00803 0.00303 -0.0312 0.3069 0.9943
5.500 0.8010 0.00825 0.00318 -0.0327 0.2867 0.9953
5.750 0.8336 0.00854 0.00335 -0.0340 0.2606 0.9965
6.000 0.8643 0.00902 0.00362 -0.0352 0.2143 0.9979
6.250 0.8914 0.00997 0.00413 -0.0359 0.1388 0.9994
6.500 0.9179 0.01034 0.00442 -0.0360 0.1241 1.0000
6.750 0.9383 0.01056 0.00464 -0.0347 0.1177 1.0000
7.000 0.9579 0.01081 0.00487 -0.0333 0.1116 1.0000
7.250 0.9778 0.01104 0.00510 -0.0318 0.1064 1.0000
7.500 0.9980 0.01122 0.00530 -0.0305 0.1019 1.0000
7.750 1.0170 0.01153 0.00557 -0.0289 0.0942 1.0000
8.000 1.0375 0.01174 0.00578 -0.0276 0.0860 1.0000
8.250 1.0550 0.01223 0.00610 -0.0259 0.0630 1.0000
8.500 1.0702 0.01293 0.00664 -0.0239 0.0413 1.0000
8.750 1.0889 0.01345 0.00713 -0.0225 0.0343 1.0000
9.000 1.1094 0.01388 0.00756 -0.0214 0.0309 1.0000
9.250 1.1296 0.01437 0.00806 -0.0202 0.0277 1.0000
9.500 1.1508 0.01479 0.00849 -0.0193 0.0256 1.0000
9.750 1.1694 0.01542 0.00913 -0.0180 0.0231 1.0000
10.000 1.1910 0.01580 0.00955 -0.0172 0.0220 1.0000
10.250 1.2114 0.01626 0.01004 -0.0163 0.0206 1.0000
10.500 1.2286 0.01694 0.01074 -0.0149 0.0191 1.0000
10.750 1.2477 0.01746 0.01130 -0.0138 0.0183 1.0000
11.000 1.2665 0.01795 0.01183 -0.0126 0.0174 1.0000
11.250 1.2831 0.01850 0.01241 -0.0112 0.0167 1.0000
11.500 1.2958 0.01919 0.01313 -0.0091 0.0159 1.0000
11.750 1.3025 0.02027 0.01428 -0.0064 0.0152 1.0000
12.000 1.3174 0.02092 0.01499 -0.0050 0.0148 1.0000
12.250 1.3308 0.02170 0.01583 -0.0035 0.0144 1.0000
12.500 1.3432 0.02258 0.01677 -0.0021 0.0140 1.0000
12.750 1.3552 0.02352 0.01776 -0.0007 0.0135 1.0000
13.000 1.3662 0.02458 0.01887 0.0005 0.0131 1.0000
13.250 1.3740 0.02595 0.02030 0.0018 0.0127 1.0000
13.500 1.3738 0.02805 0.02249 0.0034 0.0122 1.0000
13.750 1.3804 0.02971 0.02423 0.0044 0.0120 1.0000
14.000 1.3892 0.03123 0.02583 0.0050 0.0118 1.0000
14.250 1.3959 0.03299 0.02767 0.0056 0.0115 1.0000
14.500 1.4014 0.03495 0.02972 0.0061 0.0113 1.0000
14.750 1.4059 0.03707 0.03192 0.0064 0.0111 1.0000
15.000 1.4090 0.03941 0.03435 0.0066 0.0109 1.0000
15.250 1.4113 0.04194 0.03696 0.0066 0.0107 1.0000
15.500 1.4123 0.04466 0.03977 0.0064 0.0105 1.0000
15.750 1.4120 0.04761 0.04281 0.0061 0.0103 1.0000
16.000 1.4095 0.05089 0.04617 0.0056 0.0102 1.0000
16.250 1.4041 0.05460 0.04997 0.0049 0.0100 1.0000
16.500 1.3962 0.05875 0.05422 0.0039 0.0099 1.0000
16.750 1.3856 0.06341 0.05898 0.0027 0.0098 1.0000
17.000 1.3715 0.06861 0.06429 0.0013 0.0096 1.0000
17.250 1.3556 0.07422 0.07003 -0.0004 0.0095 1.0000
17.500 1.3477 0.07888 0.07479 -0.0020 0.0095 1.0000
17.750 1.3411 0.08342 0.07944 -0.0036 0.0094 1.0000
18.000 1.3336 0.08820 0.08432 -0.0054 0.0093 1.0000
18.250 1.3252 0.09321 0.08944 -0.0074 0.0093 1.0000
18.500 1.3161 0.09834 0.09467 -0.0094 0.0092 1.0000
18.750 1.3064 0.10362 0.10005 -0.0116 0.0092 1.0000
19.000 1.2966 0.10901 0.10554 -0.0139 0.0091 1.0000
19.250 1.2869 0.11447 0.11110 -0.0163 0.0090 1.0000
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