GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.35 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe614-il-1000000.txt Download as CSV file: xf-goe614-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.3638 0.08799 0.08576 -0.1051 0.9866 0.0268
-14.750 -0.3152 0.09230 0.09019 -0.1017 0.9855 0.0263
-14.500 -0.4299 0.06680 0.06428 -0.1219 0.9834 0.0256
-14.250 -0.4590 0.05659 0.05384 -0.1332 0.9818 0.0254
-14.000 -0.4775 0.05002 0.04711 -0.1395 0.9755 0.0254
-13.750 -0.4819 0.04405 0.04096 -0.1475 0.9718 0.0254
-13.500 -0.4777 0.03895 0.03569 -0.1556 0.9690 0.0256
-13.250 -0.4779 0.03514 0.03172 -0.1602 0.9592 0.0256
-13.000 -0.4595 0.03148 0.02788 -0.1678 0.9547 0.0256
-12.750 -0.4434 0.02893 0.02516 -0.1724 0.9439 0.0257
-12.500 -0.4164 0.02682 0.02288 -0.1772 0.9353 0.0258
-12.250 -0.3917 0.02525 0.02114 -0.1800 0.9240 0.0259
-12.000 -0.3773 0.02412 0.01985 -0.1798 0.9078 0.0260
-11.750 -0.3668 0.02319 0.01877 -0.1782 0.8915 0.0261
-11.500 -0.3555 0.02243 0.01786 -0.1765 0.8756 0.0262
-11.250 -0.3438 0.02171 0.01701 -0.1745 0.8619 0.0263
-11.000 -0.3303 0.02101 0.01618 -0.1727 0.8499 0.0263
-10.750 -0.3164 0.02038 0.01542 -0.1709 0.8381 0.0264
-10.500 -0.3014 0.01981 0.01476 -0.1691 0.8275 0.0265
-10.250 -0.2849 0.01930 0.01413 -0.1674 0.8174 0.0265
-10.000 -0.2681 0.01896 0.01368 -0.1658 0.8079 0.0267
-9.750 -0.2510 0.01818 0.01280 -0.1643 0.7988 0.0268
-9.500 -0.2340 0.01716 0.01175 -0.1628 0.7901 0.0269
-9.250 -0.2176 0.01635 0.01088 -0.1611 0.7809 0.0272
-9.000 -0.1995 0.01573 0.01025 -0.1596 0.7724 0.0275
-8.500 -0.1608 0.01484 0.00926 -0.1568 0.7552 0.0280
-8.250 -0.1414 0.01446 0.00880 -0.1553 0.7458 0.0281
-8.000 -0.1208 0.01407 0.00837 -0.1541 0.7366 0.0283
-7.500 -0.0798 0.01337 0.00756 -0.1514 0.7169 0.0287
-7.250 -0.0593 0.01308 0.00719 -0.1500 0.7070 0.0289
-7.000 -0.0377 0.01276 0.00682 -0.1488 0.6970 0.0291
-6.750 -0.0166 0.01250 0.00649 -0.1475 0.6867 0.0293
-6.500 0.0048 0.01223 0.00616 -0.1462 0.6756 0.0295
-6.250 0.0265 0.01199 0.00586 -0.1450 0.6647 0.0298
-5.750 0.0704 0.01157 0.00530 -0.1426 0.6430 0.0302
-5.500 0.0924 0.01141 0.00506 -0.1413 0.6328 0.0304
-5.250 0.1153 0.01124 0.00484 -0.1403 0.6225 0.0306
-5.000 0.1379 0.01110 0.00463 -0.1392 0.6128 0.0308
-4.750 0.1591 0.01081 0.00426 -0.1378 0.6027 0.0313
-4.500 0.1814 0.01061 0.00400 -0.1367 0.5934 0.0319
-4.250 0.2038 0.01047 0.00380 -0.1355 0.5836 0.0325
-4.000 0.2271 0.01035 0.00363 -0.1345 0.5752 0.0332
-3.750 0.2502 0.01026 0.00349 -0.1334 0.5664 0.0338
-3.500 0.2736 0.01018 0.00335 -0.1324 0.5588 0.0344
-3.250 0.2974 0.01010 0.00324 -0.1315 0.5512 0.0350
-3.000 0.3196 0.01005 0.00312 -0.1303 0.5435 0.0358
-2.750 0.3440 0.00994 0.00300 -0.1294 0.5372 0.0373
-2.500 0.3663 0.00990 0.00290 -0.1282 0.5299 0.0392
-2.250 0.3877 0.00981 0.00280 -0.1268 0.5226 0.0448
-2.000 0.4074 0.00950 0.00268 -0.1252 0.5160 0.1005
-1.750 0.4273 0.00947 0.00264 -0.1235 0.5083 0.1139
-1.500 0.4498 0.00932 0.00257 -0.1224 0.5030 0.1367
-1.250 0.4714 0.00917 0.00257 -0.1212 0.4975 0.1855
-1.000 0.4927 0.00919 0.00260 -0.1198 0.4912 0.2032
-0.750 0.5161 0.00918 0.00262 -0.1189 0.4865 0.2176
-0.500 0.5392 0.00919 0.00264 -0.1178 0.4804 0.2277
-0.250 0.5611 0.00926 0.00269 -0.1166 0.4747 0.2368
0.000 0.5838 0.00930 0.00274 -0.1155 0.4690 0.2474
0.250 0.6076 0.00934 0.00278 -0.1146 0.4636 0.2570
0.500 0.6292 0.00940 0.00285 -0.1134 0.4573 0.2699
0.750 0.6514 0.00947 0.00293 -0.1122 0.4525 0.2841
1.000 0.6751 0.00948 0.00299 -0.1114 0.4482 0.3007
1.250 0.6972 0.00952 0.00307 -0.1103 0.4431 0.3222
1.500 0.7177 0.00961 0.00318 -0.1088 0.4376 0.3454
1.750 0.7406 0.00964 0.00327 -0.1079 0.4336 0.3713
2.000 0.7637 0.00967 0.00337 -0.1069 0.4299 0.3964
2.250 0.7858 0.00974 0.00347 -0.1058 0.4258 0.4185
2.500 0.8064 0.00983 0.00360 -0.1045 0.4216 0.4416
2.750 0.8274 0.00992 0.00373 -0.1032 0.4174 0.4659
3.000 0.8503 0.00995 0.00384 -0.1023 0.4141 0.4933
3.250 0.8719 0.01000 0.00397 -0.1011 0.4102 0.5260
3.500 0.8915 0.01009 0.00412 -0.0996 0.4054 0.5611
3.750 0.9099 0.01020 0.00430 -0.0979 0.4009 0.5976
4.000 0.9300 0.01017 0.00444 -0.0964 0.3978 0.6554
4.250 0.9437 0.01002 0.00463 -0.0936 0.3940 0.7788
4.500 1.0560 0.01011 0.00504 -0.1121 0.3855 1.0000
4.750 1.0780 0.01027 0.00518 -0.1111 0.3817 1.0000
5.000 1.0999 0.01044 0.00533 -0.1101 0.3774 1.0000
5.250 1.1207 0.01064 0.00551 -0.1090 0.3728 1.0000
5.500 1.1401 0.01091 0.00573 -0.1076 0.3676 1.0000
5.750 1.1627 0.01108 0.00590 -0.1068 0.3640 1.0000
6.000 1.1838 0.01130 0.00610 -0.1058 0.3587 1.0000
6.250 1.2023 0.01162 0.00637 -0.1043 0.3520 1.0000
6.500 1.2237 0.01185 0.00659 -0.1034 0.3472 1.0000
6.750 1.2440 0.01213 0.00685 -0.1024 0.3410 1.0000
7.000 1.2616 0.01251 0.00718 -0.1009 0.3344 1.0000
7.250 1.2827 0.01278 0.00744 -0.1000 0.3288 1.0000
7.500 1.3005 0.01318 0.00781 -0.0987 0.3207 1.0000
7.750 1.3187 0.01358 0.00818 -0.0974 0.3131 1.0000
8.000 1.3348 0.01408 0.00863 -0.0959 0.3036 1.0000
8.250 1.3517 0.01456 0.00908 -0.0945 0.2943 1.0000
8.500 1.3665 0.01516 0.00962 -0.0929 0.2852 1.0000
8.750 1.3807 0.01579 0.01021 -0.0913 0.2744 1.0000
9.000 1.3954 0.01643 0.01081 -0.0898 0.2661 1.0000
9.250 1.4073 0.01723 0.01155 -0.0880 0.2562 1.0000
9.500 1.4218 0.01791 0.01222 -0.0866 0.2482 1.0000
9.750 1.4338 0.01875 0.01303 -0.0850 0.2410 1.0000
10.000 1.4467 0.01956 0.01382 -0.0835 0.2328 1.0000
10.250 1.4570 0.02055 0.01478 -0.0819 0.2254 1.0000
10.500 1.4706 0.02138 0.01560 -0.0806 0.2192 1.0000
10.750 1.4782 0.02260 0.01678 -0.0788 0.2105 1.0000
11.000 1.4900 0.02358 0.01775 -0.0775 0.2040 1.0000
11.250 1.4979 0.02485 0.01900 -0.0759 0.1966 1.0000
11.500 1.5074 0.02606 0.02020 -0.0746 0.1886 1.0000
11.750 1.5110 0.02771 0.02180 -0.0728 0.1764 1.0000
12.000 1.4923 0.03107 0.02498 -0.0695 0.1423 1.0000
12.250 1.4790 0.03425 0.02808 -0.0669 0.1248 1.0000
12.500 1.4804 0.03635 0.03018 -0.0656 0.1198 1.0000
12.750 1.4839 0.03835 0.03222 -0.0645 0.1175 1.0000
13.000 1.4911 0.04008 0.03399 -0.0637 0.1167 1.0000
13.250 1.4935 0.04226 0.03620 -0.0627 0.1145 1.0000
13.500 1.4979 0.04431 0.03829 -0.0619 0.1130 1.0000
13.750 1.5010 0.04651 0.04054 -0.0611 0.1117 1.0000
14.000 1.5034 0.04884 0.04292 -0.0604 0.1100 1.0000
14.250 1.5095 0.05081 0.04495 -0.0599 0.1095 1.0000
14.500 1.5136 0.05303 0.04724 -0.0594 0.1090 1.0000
14.750 1.5177 0.05523 0.04950 -0.0589 0.1083 1.0000
15.000 1.5200 0.05766 0.05199 -0.0584 0.1075 1.0000
15.250 1.5218 0.06017 0.05457 -0.0580 0.1069 1.0000
15.500 1.5235 0.06271 0.05718 -0.0577 0.1062 1.0000
15.750 1.5234 0.06549 0.06001 -0.0573 0.1054 1.0000
16.000 1.5217 0.06844 0.06303 -0.0570 0.1046 1.0000
16.250 1.5202 0.07138 0.06603 -0.0567 0.1036 1.0000
16.500 1.5179 0.07449 0.06919 -0.0565 0.1028 1.0000
16.750 1.5132 0.07789 0.07267 -0.0564 0.1016 1.0000
17.000 1.5097 0.08115 0.07598 -0.0563 0.1004 1.0000
17.250 1.5024 0.08490 0.07980 -0.0563 0.0990 1.0000
17.500 1.5024 0.08779 0.08276 -0.0563 0.0985 1.0000
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