GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 619 AIRFOIL (goe619-il) Reynolds number: 500,000 Max Cl/Cd: 99.66 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe619-il-500000.txt Download as CSV file: xf-goe619-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 619 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6646 0.06736 0.06435 -0.0771 1.0000 0.0322
-13.250 -0.7012 0.05908 0.05592 -0.0832 1.0000 0.0320
-13.000 -0.7338 0.05219 0.04891 -0.0879 1.0000 0.0319
-12.750 -0.7687 0.04595 0.04255 -0.0918 1.0000 0.0318
-12.500 -0.8106 0.04224 0.03877 -0.0911 1.0000 0.0317
-12.250 -0.8064 0.03860 0.03482 -0.0965 0.9948 0.0319
-12.000 -0.7975 0.03345 0.02935 -0.1012 0.9884 0.0324
-11.750 -0.7737 0.03099 0.02678 -0.1039 0.9847 0.0329
-11.500 -0.7451 0.02912 0.02479 -0.1066 0.9823 0.0334
-11.250 -0.7230 0.02762 0.02318 -0.1074 0.9763 0.0338
-11.000 -0.6939 0.02624 0.02168 -0.1093 0.9728 0.0345
-10.750 -0.6625 0.02486 0.02017 -0.1115 0.9705 0.0351
-10.500 -0.6377 0.02363 0.01879 -0.1120 0.9650 0.0357
-10.250 -0.6090 0.02242 0.01744 -0.1132 0.9608 0.0362
-10.000 -0.5767 0.02131 0.01617 -0.1149 0.9582 0.0366
-9.750 -0.5419 0.02034 0.01506 -0.1169 0.9563 0.0370
-9.500 -0.5177 0.01900 0.01360 -0.1169 0.9497 0.0376
-9.250 -0.4875 0.01778 0.01234 -0.1182 0.9453 0.0384
-9.000 -0.4534 0.01692 0.01143 -0.1199 0.9420 0.0392
-8.750 -0.4253 0.01621 0.01066 -0.1202 0.9349 0.0399
-8.500 -0.3938 0.01551 0.00990 -0.1211 0.9288 0.0406
-8.250 -0.3622 0.01489 0.00919 -0.1221 0.9225 0.0413
-8.000 -0.3343 0.01436 0.00857 -0.1221 0.9139 0.0421
-7.750 -0.3040 0.01388 0.00799 -0.1226 0.9066 0.0428
-7.500 -0.2792 0.01326 0.00730 -0.1221 0.8969 0.0439
-7.250 -0.2528 0.01277 0.00677 -0.1219 0.8880 0.0453
-7.000 -0.2263 0.01240 0.00633 -0.1216 0.8788 0.0466
-6.750 -0.2004 0.01208 0.00594 -0.1211 0.8700 0.0481
-6.500 -0.1738 0.01177 0.00554 -0.1207 0.8613 0.0498
-6.250 -0.1488 0.01141 0.00517 -0.1200 0.8521 0.0529
-6.000 -0.1221 0.01114 0.00484 -0.1196 0.8436 0.0576
-5.750 -0.0968 0.01086 0.00462 -0.1190 0.8348 0.0677
-5.500 -0.0695 0.01071 0.00448 -0.1187 0.8266 0.0822
-5.250 -0.0431 0.01061 0.00437 -0.1182 0.8179 0.0916
-5.000 -0.0151 0.01062 0.00427 -0.1179 0.8099 0.0974
-4.750 0.0106 0.01041 0.00408 -0.1174 0.8015 0.1035
-4.500 0.0376 0.01033 0.00393 -0.1170 0.7935 0.1081
-4.250 0.0644 0.01027 0.00380 -0.1166 0.7855 0.1115
-4.000 0.0904 0.01007 0.00359 -0.1161 0.7774 0.1172
-3.750 0.1171 0.00997 0.00346 -0.1156 0.7696 0.1221
-3.500 0.1436 0.00987 0.00331 -0.1151 0.7613 0.1266
-3.250 0.1699 0.00972 0.00316 -0.1147 0.7536 0.1337
-3.000 0.1960 0.00962 0.00303 -0.1141 0.7447 0.1410
-2.750 0.2219 0.00947 0.00290 -0.1135 0.7352 0.1523
-2.500 0.2474 0.00935 0.00278 -0.1128 0.7242 0.1712
-2.250 0.2726 0.00921 0.00273 -0.1121 0.7132 0.2000
-2.000 0.2989 0.00916 0.00269 -0.1116 0.7046 0.2239
-1.750 0.3254 0.00911 0.00268 -0.1111 0.6966 0.2423
-1.250 0.3789 0.00909 0.00264 -0.1102 0.6814 0.2688
-1.000 0.4054 0.00908 0.00262 -0.1098 0.6743 0.2801
-0.750 0.4322 0.00907 0.00261 -0.1094 0.6672 0.2911
-0.500 0.4587 0.00907 0.00261 -0.1089 0.6597 0.3019
-0.250 0.4851 0.00906 0.00260 -0.1084 0.6524 0.3124
0.000 0.5114 0.00906 0.00259 -0.1079 0.6441 0.3233
0.250 0.5374 0.00905 0.00260 -0.1073 0.6362 0.3357
0.500 0.5632 0.00903 0.00261 -0.1067 0.6272 0.3496
0.750 0.5890 0.00904 0.00264 -0.1061 0.6193 0.3668
1.000 0.6146 0.00902 0.00267 -0.1055 0.6102 0.3879
1.250 0.6400 0.00902 0.00271 -0.1049 0.6014 0.4098
1.500 0.6650 0.00901 0.00275 -0.1041 0.5916 0.4356
1.750 0.6897 0.00898 0.00280 -0.1034 0.5815 0.4689
2.000 0.7132 0.00893 0.00284 -0.1024 0.5705 0.5126
2.250 0.7290 0.00838 0.00296 -0.0998 0.5585 0.7262
2.500 0.8081 0.00818 0.00316 -0.1105 0.5369 1.0000
2.750 0.8291 0.00833 0.00322 -0.1090 0.5190 1.0000
3.000 0.8491 0.00852 0.00330 -0.1072 0.4971 1.0000
3.250 0.8673 0.00878 0.00341 -0.1052 0.4719 1.0000
3.500 0.8855 0.00907 0.00355 -0.1032 0.4444 1.0000
3.750 0.9033 0.00940 0.00373 -0.1011 0.4189 1.0000
4.000 0.9212 0.00975 0.00393 -0.0991 0.3938 1.0000
4.250 0.9392 0.01010 0.00414 -0.0971 0.3721 1.0000
4.500 0.9577 0.01044 0.00436 -0.0953 0.3515 1.0000
4.750 0.9763 0.01078 0.00459 -0.0935 0.3334 1.0000
5.000 0.9950 0.01111 0.00482 -0.0917 0.3181 1.0000
5.250 1.0136 0.01143 0.00507 -0.0899 0.3061 1.0000
5.500 1.0333 0.01171 0.00530 -0.0883 0.2958 1.0000
5.750 1.0518 0.01200 0.00554 -0.0865 0.2871 1.0000
6.000 1.0695 0.01229 0.00579 -0.0845 0.2793 1.0000
6.250 1.0870 0.01258 0.00605 -0.0825 0.2728 1.0000
6.500 1.1057 0.01284 0.00630 -0.0808 0.2663 1.0000
6.750 1.1222 0.01320 0.00660 -0.0787 0.2601 1.0000
7.000 1.1417 0.01345 0.00687 -0.0772 0.2550 1.0000
7.250 1.1603 0.01374 0.00716 -0.0755 0.2501 1.0000
7.500 1.1768 0.01413 0.00750 -0.0736 0.2444 1.0000
7.750 1.1962 0.01440 0.00779 -0.0721 0.2386 1.0000
8.000 1.2142 0.01473 0.00812 -0.0705 0.2328 1.0000
8.250 1.2298 0.01518 0.00852 -0.0685 0.2269 1.0000
8.500 1.2500 0.01544 0.00882 -0.0673 0.2218 1.0000
8.750 1.2674 0.01582 0.00920 -0.0657 0.2166 1.0000
9.000 1.2827 0.01630 0.00966 -0.0639 0.2112 1.0000
9.250 1.3023 0.01661 0.01001 -0.0626 0.2065 1.0000
9.500 1.3184 0.01708 0.01047 -0.0610 0.2001 1.0000
9.750 1.3349 0.01755 0.01095 -0.0594 0.1941 1.0000
10.000 1.3520 0.01800 0.01141 -0.0580 0.1873 1.0000
10.250 1.3668 0.01858 0.01197 -0.0564 0.1787 1.0000
10.500 1.3802 0.01926 0.01260 -0.0546 0.1663 1.0000
10.750 1.3919 0.02006 0.01333 -0.0528 0.1492 1.0000
11.000 1.3954 0.02138 0.01447 -0.0502 0.1216 1.0000
11.250 1.3921 0.02323 0.01611 -0.0471 0.0914 1.0000
11.500 1.3932 0.02489 0.01767 -0.0446 0.0755 1.0000
11.750 1.3997 0.02624 0.01901 -0.0428 0.0691 1.0000
12.000 1.4085 0.02746 0.02025 -0.0413 0.0660 1.0000
12.250 1.4152 0.02890 0.02170 -0.0397 0.0624 1.0000
12.500 1.4249 0.03012 0.02298 -0.0385 0.0600 1.0000
12.750 1.4337 0.03145 0.02436 -0.0373 0.0581 1.0000
13.000 1.4392 0.03309 0.02603 -0.0360 0.0556 1.0000
13.250 1.4447 0.03479 0.02776 -0.0348 0.0531 1.0000
13.500 1.4555 0.03606 0.02910 -0.0340 0.0512 1.0000
13.750 1.4625 0.03770 0.03078 -0.0331 0.0488 1.0000
14.000 1.4671 0.03961 0.03273 -0.0322 0.0468 1.0000
14.250 1.4746 0.04129 0.03446 -0.0315 0.0446 1.0000
14.500 1.4820 0.04301 0.03624 -0.0309 0.0419 1.0000
14.750 1.4855 0.04517 0.03841 -0.0302 0.0379 1.0000
15.000 1.4868 0.04762 0.04085 -0.0297 0.0276 1.0000
15.250 1.4756 0.05148 0.04466 -0.0292 0.0193 1.0000
15.500 1.4660 0.05535 0.04861 -0.0290 0.0173 1.0000
15.750 1.4598 0.05898 0.05234 -0.0290 0.0166 1.0000
16.000 1.4540 0.06267 0.05614 -0.0291 0.0161 1.0000
16.250 1.4478 0.06650 0.06008 -0.0295 0.0157 1.0000
16.500 1.4391 0.07079 0.06449 -0.0300 0.0153 1.0000
16.750 1.4326 0.07489 0.06870 -0.0307 0.0151 1.0000
17.000 1.4244 0.07933 0.07328 -0.0316 0.0149 1.0000
17.250 1.4158 0.08393 0.07799 -0.0327 0.0147 1.0000
17.500 1.4058 0.08885 0.08305 -0.0340 0.0145 1.0000
17.750 1.3944 0.09410 0.08842 -0.0356 0.0144 1.0000
18.000 1.3826 0.09949 0.09394 -0.0373 0.0143 1.0000
18.250 1.3705 0.10502 0.09959 -0.0393 0.0142 1.0000
18.500 1.3584 0.11065 0.10535 -0.0413 0.0141 1.0000
18.750 1.3447 0.11664 0.11145 -0.0437 0.0139 1.0000
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