GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.05 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe677-il-1000000.txt Download as CSV file: xf-goe677-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.2549 0.05313 0.05064 -0.0435 1.0000 0.0156
-16.250 -1.2867 0.04528 0.04255 -0.0482 1.0000 0.0156
-16.000 -1.2998 0.04134 0.03843 -0.0486 1.0000 0.0157
-15.750 -1.3052 0.03860 0.03553 -0.0478 1.0000 0.0159
-15.500 -1.3058 0.03650 0.03329 -0.0465 1.0000 0.0160
-15.250 -1.3159 0.03388 0.03050 -0.0440 1.0000 0.0163
-15.000 -1.3184 0.03203 0.02855 -0.0414 1.0000 0.0167
-14.750 -1.3105 0.03098 0.02745 -0.0394 1.0000 0.0170
-14.500 -1.2972 0.03034 0.02678 -0.0378 1.0000 0.0174
-14.250 -1.2826 0.02981 0.02623 -0.0361 1.0000 0.0177
-14.000 -1.2687 0.02921 0.02557 -0.0344 1.0000 0.0181
-13.750 -1.2529 0.02856 0.02484 -0.0330 1.0000 0.0185
-13.500 -1.2366 0.02782 0.02401 -0.0317 1.0000 0.0190
-13.250 -1.2196 0.02707 0.02316 -0.0304 1.0000 0.0193
-13.000 -1.2005 0.02649 0.02248 -0.0293 1.0000 0.0196
-12.750 -1.1917 0.02478 0.02060 -0.0271 1.0000 0.0201
-12.500 -1.1740 0.02401 0.01978 -0.0259 1.0000 0.0206
-12.250 -1.1524 0.02363 0.01939 -0.0251 1.0000 0.0210
-12.000 -1.1299 0.02334 0.01908 -0.0244 1.0000 0.0215
-11.750 -1.1072 0.02304 0.01876 -0.0237 1.0000 0.0220
-11.500 -1.0850 0.02263 0.01829 -0.0230 1.0000 0.0225
-11.250 -1.0630 0.02215 0.01773 -0.0222 1.0000 0.0230
-11.000 -1.0408 0.02168 0.01717 -0.0214 1.0000 0.0234
-10.750 -1.0178 0.02130 0.01672 -0.0207 1.0000 0.0237
-10.500 -1.0019 0.01973 0.01496 -0.0192 1.0000 0.0244
-10.250 -0.9805 0.01908 0.01428 -0.0183 1.0000 0.0250
-10.000 -0.9567 0.01881 0.01402 -0.0177 1.0000 0.0255
-9.750 -0.9331 0.01851 0.01369 -0.0170 1.0000 0.0260
-9.500 -0.9100 0.01811 0.01325 -0.0162 1.0000 0.0266
-9.250 -0.8871 0.01769 0.01277 -0.0154 1.0000 0.0271
-9.000 -0.8643 0.01732 0.01235 -0.0145 1.0000 0.0277
-8.500 -0.8035 0.01660 0.01150 -0.0160 0.9901 0.0286
-8.250 -0.7738 0.01517 0.00992 -0.0170 0.9743 0.0295
-8.000 -0.7429 0.01462 0.00934 -0.0178 0.9475 0.0303
-7.750 -0.7190 0.01433 0.00893 -0.0168 0.9137 0.0309
-7.500 -0.6957 0.01406 0.00854 -0.0158 0.8835 0.0314
-7.250 -0.6715 0.01383 0.00817 -0.0150 0.8522 0.0321
-7.000 -0.6469 0.01361 0.00780 -0.0143 0.8161 0.0328
-6.750 -0.6219 0.01336 0.00736 -0.0137 0.7819 0.0334
-6.500 -0.5962 0.01310 0.00697 -0.0132 0.7568 0.0338
-6.250 -0.5700 0.01287 0.00662 -0.0129 0.7390 0.0342
-6.000 -0.5446 0.01240 0.00605 -0.0124 0.7254 0.0348
-5.750 -0.5201 0.01182 0.00538 -0.0118 0.7147 0.0360
-5.500 -0.4935 0.01155 0.00508 -0.0116 0.7058 0.0370
-5.250 -0.4667 0.01133 0.00481 -0.0114 0.6984 0.0378
-5.000 -0.4396 0.01111 0.00455 -0.0112 0.6913 0.0387
-4.750 -0.4126 0.01091 0.00429 -0.0110 0.6846 0.0397
-4.500 -0.3852 0.01071 0.00406 -0.0108 0.6794 0.0406
-4.250 -0.3576 0.01056 0.00387 -0.0107 0.6744 0.0412
-4.000 -0.3317 0.01017 0.00343 -0.0103 0.6692 0.0434
-3.750 -0.3043 0.00999 0.00326 -0.0102 0.6643 0.0453
-3.500 -0.2765 0.00984 0.00310 -0.0102 0.6595 0.0472
-3.250 -0.2487 0.00973 0.00295 -0.0101 0.6554 0.0488
-3.000 -0.2215 0.00953 0.00271 -0.0099 0.6514 0.0518
-2.750 -0.1937 0.00936 0.00258 -0.0099 0.6481 0.0553
-2.500 -0.1655 0.00925 0.00247 -0.0099 0.6444 0.0583
-2.250 -0.1379 0.00909 0.00231 -0.0099 0.6404 0.0628
-2.000 -0.1101 0.00899 0.00220 -0.0098 0.6363 0.0678
-1.750 -0.0818 0.00891 0.00211 -0.0099 0.6327 0.0710
-1.500 -0.0540 0.00873 0.00198 -0.0098 0.6292 0.0792
-1.250 -0.0259 0.00861 0.00187 -0.0098 0.6253 0.0867
-1.000 0.0015 0.00846 0.00180 -0.0098 0.6213 0.1078
-0.750 0.0288 0.00827 0.00174 -0.0097 0.6172 0.1476
-0.500 0.0558 0.00798 0.00165 -0.0096 0.6130 0.2001
-0.250 0.0810 0.00754 0.00158 -0.0092 0.6086 0.3186
0.000 0.1019 0.00670 0.00146 -0.0082 0.6043 0.5377
0.250 0.1143 0.00556 0.00145 -0.0048 0.6002 0.8536
0.500 0.1404 0.00554 0.00154 -0.0040 0.5940 0.8963
1.000 0.1942 0.00564 0.00164 -0.0031 0.5796 0.9273
1.250 0.2209 0.00572 0.00168 -0.0026 0.5723 0.9369
1.500 0.2480 0.00578 0.00175 -0.0022 0.5645 0.9446
1.750 0.2726 0.00590 0.00183 -0.0012 0.5547 0.9548
2.000 0.3017 0.00600 0.00189 -0.0012 0.5399 0.9597
2.250 0.3310 0.00613 0.00195 -0.0013 0.5194 0.9644
2.500 0.3577 0.00633 0.00203 -0.0009 0.4904 0.9704
2.750 0.3954 0.00663 0.00219 -0.0031 0.4606 0.9732
3.000 0.4321 0.00685 0.00232 -0.0051 0.4420 0.9748
3.250 0.4701 0.00706 0.00246 -0.0074 0.4290 0.9765
3.500 0.5050 0.00724 0.00258 -0.0090 0.4180 0.9787
3.750 0.5339 0.00735 0.00267 -0.0093 0.4093 0.9813
4.000 0.5662 0.00750 0.00277 -0.0103 0.4006 0.9831
4.250 0.6019 0.00758 0.00285 -0.0122 0.3928 0.9838
4.500 0.6340 0.00769 0.00293 -0.0132 0.3838 0.9844
4.750 0.6658 0.00777 0.00300 -0.0143 0.3741 0.9851
5.000 0.6972 0.00787 0.00308 -0.0152 0.3644 0.9858
5.250 0.7282 0.00800 0.00317 -0.0161 0.3515 0.9866
5.500 0.7591 0.00815 0.00327 -0.0169 0.3352 0.9875
5.750 0.7891 0.00839 0.00340 -0.0177 0.3075 0.9886
6.000 0.8171 0.00884 0.00363 -0.0182 0.2596 0.9898
6.250 0.8429 0.00948 0.00398 -0.0184 0.2052 0.9912
6.750 0.8932 0.01075 0.00477 -0.0185 0.1151 0.9940
7.000 0.9222 0.01119 0.00510 -0.0192 0.0968 0.9946
7.250 0.9521 0.01148 0.00538 -0.0200 0.0897 0.9953
7.500 0.9819 0.01178 0.00566 -0.0209 0.0855 0.9961
7.750 1.0114 0.01213 0.00599 -0.0216 0.0804 0.9970
8.000 1.0415 0.01234 0.00625 -0.0224 0.0783 0.9979
8.250 1.0711 0.01257 0.00650 -0.0232 0.0752 0.9988
8.500 1.0996 0.01293 0.00682 -0.0238 0.0697 0.9996
8.750 1.1246 0.01316 0.00708 -0.0236 0.0659 1.0000
9.000 1.1434 0.01344 0.00733 -0.0222 0.0586 1.0000
9.250 1.1564 0.01409 0.00778 -0.0198 0.0350 1.0000
9.500 1.1656 0.01489 0.00848 -0.0168 0.0215 1.0000
9.750 1.1773 0.01544 0.00903 -0.0140 0.0187 1.0000
10.000 1.1905 0.01584 0.00948 -0.0115 0.0176 1.0000
10.250 1.2021 0.01631 0.00998 -0.0088 0.0165 1.0000
10.500 1.2121 0.01688 0.01058 -0.0058 0.0155 1.0000
10.750 1.2228 0.01745 0.01120 -0.0031 0.0148 1.0000
11.000 1.2359 0.01795 0.01174 -0.0008 0.0144 1.0000
11.250 1.2488 0.01853 0.01237 0.0013 0.0139 1.0000
11.500 1.2584 0.01916 0.01305 0.0040 0.0135 1.0000
11.750 1.2674 0.01991 0.01385 0.0065 0.0131 1.0000
12.000 1.2753 0.02088 0.01488 0.0087 0.0126 1.0000
12.250 1.2789 0.02229 0.01637 0.0109 0.0122 1.0000
12.500 1.2864 0.02360 0.01775 0.0124 0.0119 1.0000
12.750 1.2980 0.02469 0.01891 0.0133 0.0117 1.0000
13.000 1.3082 0.02598 0.02027 0.0141 0.0114 1.0000
13.250 1.3174 0.02743 0.02180 0.0148 0.0111 1.0000
13.500 1.3256 0.02906 0.02349 0.0153 0.0108 1.0000
13.750 1.3324 0.03089 0.02539 0.0157 0.0106 1.0000
14.000 1.3383 0.03287 0.02744 0.0159 0.0104 1.0000
14.250 1.3424 0.03508 0.02972 0.0161 0.0102 1.0000
14.500 1.3445 0.03754 0.03227 0.0162 0.0100 1.0000
14.750 1.3424 0.04046 0.03526 0.0162 0.0098 1.0000
15.000 1.3367 0.04381 0.03871 0.0161 0.0096 1.0000
15.250 1.3251 0.04783 0.04284 0.0160 0.0095 1.0000
15.500 1.3194 0.05130 0.04642 0.0157 0.0094 1.0000
15.750 1.3192 0.05428 0.04948 0.0153 0.0093 1.0000
16.000 1.3185 0.05742 0.05271 0.0147 0.0092 1.0000
16.250 1.3165 0.06083 0.05621 0.0139 0.0091 1.0000
16.500 1.3140 0.06444 0.05991 0.0129 0.0090 1.0000
16.750 1.3099 0.06830 0.06387 0.0119 0.0090 1.0000
17.000 1.3055 0.07231 0.06797 0.0106 0.0089 1.0000
17.250 1.3000 0.07656 0.07232 0.0093 0.0088 1.0000
17.500 1.2938 0.08096 0.07681 0.0078 0.0087 1.0000
17.750 1.2871 0.08546 0.08141 0.0062 0.0086 1.0000
18.000 1.2800 0.09010 0.08614 0.0046 0.0085 1.0000
18.250 1.2725 0.09487 0.09100 0.0028 0.0084 1.0000
18.500 1.2645 0.09973 0.09596 0.0009 0.0084 1.0000
18.750 1.2562 0.10469 0.10101 -0.0011 0.0083 1.0000
19.000 1.2481 0.10974 0.10614 -0.0032 0.0082 1.0000
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