GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 619 AIRFOIL (goe619-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.86 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe619-il-1000000.txt Download as CSV file: xf-goe619-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6298 0.11045 0.10829 -0.0526 1.0000 0.0234
-16.000 -0.7364 0.08677 0.08427 -0.0671 1.0000 0.0234
-15.750 -0.7726 0.07759 0.07496 -0.0727 1.0000 0.0234
-15.500 -0.8009 0.07033 0.06759 -0.0771 1.0000 0.0235
-15.250 -0.8225 0.06440 0.06156 -0.0805 1.0000 0.0234
-15.000 -0.8485 0.05834 0.05541 -0.0838 1.0000 0.0236
-14.750 -0.8704 0.05304 0.05005 -0.0865 1.0000 0.0237
-14.500 -0.8952 0.04753 0.04444 -0.0893 1.0000 0.0238
-14.250 -0.9168 0.04257 0.03942 -0.0916 1.0000 0.0239
-14.000 -0.9430 0.03675 0.03347 -0.0953 1.0000 0.0238
-13.750 -0.9593 0.03200 0.02856 -0.1001 0.9983 0.0239
-13.500 -0.9369 0.02982 0.02629 -0.1038 0.9951 0.0242
-13.250 -0.9107 0.02803 0.02442 -0.1069 0.9926 0.0245
-13.000 -0.8872 0.02660 0.02291 -0.1085 0.9889 0.0248
-12.750 -0.8602 0.02533 0.02155 -0.1105 0.9860 0.0252
-12.500 -0.8314 0.02415 0.02028 -0.1125 0.9840 0.0255
-12.250 -0.8007 0.02311 0.01915 -0.1145 0.9825 0.0260
-12.000 -0.7778 0.02220 0.01816 -0.1147 0.9774 0.0264
-11.750 -0.7494 0.02131 0.01717 -0.1159 0.9741 0.0267
-11.500 -0.7191 0.02043 0.01621 -0.1173 0.9718 0.0270
-11.250 -0.6867 0.01975 0.01544 -0.1188 0.9701 0.0272
-11.000 -0.6660 0.01845 0.01403 -0.1186 0.9633 0.0277
-10.750 -0.6376 0.01721 0.01273 -0.1199 0.9590 0.0282
-10.500 -0.6036 0.01633 0.01180 -0.1218 0.9562 0.0286
-10.250 -0.5763 0.01569 0.01111 -0.1222 0.9485 0.0290
-10.000 -0.5431 0.01503 0.01039 -0.1237 0.9429 0.0294
-9.750 -0.5128 0.01446 0.00976 -0.1245 0.9346 0.0299
-9.500 -0.4812 0.01393 0.00914 -0.1255 0.9260 0.0303
-9.250 -0.4541 0.01351 0.00864 -0.1255 0.9151 0.0308
-9.000 -0.4268 0.01312 0.00817 -0.1255 0.9052 0.0313
-8.750 -0.4008 0.01277 0.00772 -0.1252 0.8946 0.0316
-8.500 -0.3758 0.01245 0.00733 -0.1246 0.8843 0.0318
-8.250 -0.3517 0.01202 0.00679 -0.1239 0.8742 0.0322
-8.000 -0.3292 0.01148 0.00616 -0.1229 0.8636 0.0329
-7.750 -0.3049 0.01111 0.00572 -0.1222 0.8545 0.0335
-7.500 -0.2801 0.01080 0.00535 -0.1216 0.8451 0.0342
-7.250 -0.2548 0.01053 0.00502 -0.1209 0.8362 0.0348
-7.000 -0.2294 0.01031 0.00472 -0.1203 0.8269 0.0355
-6.750 -0.2036 0.01009 0.00444 -0.1198 0.8182 0.0363
-6.500 -0.1778 0.00990 0.00418 -0.1192 0.8094 0.0369
-6.250 -0.1521 0.00965 0.00388 -0.1186 0.8009 0.0379
-6.000 -0.1266 0.00941 0.00358 -0.1180 0.7922 0.0396
-5.750 -0.1004 0.00920 0.00334 -0.1175 0.7839 0.0412
-5.500 -0.0744 0.00903 0.00312 -0.1169 0.7753 0.0437
-5.250 -0.0486 0.00877 0.00289 -0.1164 0.7671 0.0522
-5.000 -0.0230 0.00855 0.00275 -0.1158 0.7587 0.0739
-4.750 0.0039 0.00844 0.00267 -0.1155 0.7506 0.0831
-4.500 0.0306 0.00839 0.00257 -0.1150 0.7421 0.0883
-4.250 0.0575 0.00830 0.00249 -0.1146 0.7340 0.0931
-4.000 0.0844 0.00828 0.00241 -0.1142 0.7253 0.0964
-3.750 0.1113 0.00821 0.00231 -0.1138 0.7162 0.0997
-3.500 0.1372 0.00814 0.00220 -0.1132 0.7050 0.1040
-3.250 0.1635 0.00809 0.00211 -0.1127 0.6930 0.1075
-3.000 0.1902 0.00806 0.00203 -0.1122 0.6826 0.1104
-2.750 0.2164 0.00800 0.00194 -0.1117 0.6735 0.1161
-2.500 0.2435 0.00790 0.00186 -0.1113 0.6661 0.1228
-2.250 0.2700 0.00782 0.00179 -0.1109 0.6588 0.1327
-2.000 0.2965 0.00770 0.00172 -0.1105 0.6524 0.1532
-1.750 0.3230 0.00757 0.00169 -0.1101 0.6455 0.1870
-1.250 0.3767 0.00747 0.00167 -0.1093 0.6318 0.2238
-1.000 0.4033 0.00747 0.00166 -0.1089 0.6240 0.2374
-0.750 0.4303 0.00745 0.00167 -0.1085 0.6166 0.2504
-0.500 0.4570 0.00745 0.00166 -0.1081 0.6089 0.2601
-0.250 0.4839 0.00747 0.00167 -0.1077 0.6017 0.2694
0.000 0.5107 0.00746 0.00168 -0.1073 0.5936 0.2800
0.250 0.5372 0.00749 0.00169 -0.1069 0.5857 0.2897
0.500 0.5639 0.00749 0.00171 -0.1064 0.5766 0.3006
0.750 0.5901 0.00752 0.00174 -0.1059 0.5675 0.3118
1.250 0.6421 0.00758 0.00180 -0.1049 0.5448 0.3397
1.500 0.6673 0.00762 0.00185 -0.1042 0.5307 0.3572
1.750 0.6919 0.00769 0.00191 -0.1034 0.5138 0.3773
2.000 0.7161 0.00777 0.00199 -0.1026 0.4956 0.4017
2.250 0.7385 0.00793 0.00209 -0.1014 0.4692 0.4288
2.500 0.7601 0.00812 0.00222 -0.1001 0.4403 0.4576
2.750 0.7819 0.00828 0.00236 -0.0989 0.4140 0.4935
3.000 0.8013 0.00834 0.00253 -0.0972 0.3887 0.5752
3.250 0.8676 0.00797 0.00295 -0.1058 0.3572 0.9992
3.500 0.8897 0.00823 0.00310 -0.1046 0.3383 1.0000
3.750 0.9103 0.00848 0.00325 -0.1031 0.3215 1.0000
4.000 0.9308 0.00873 0.00341 -0.1015 0.3056 1.0000
4.500 0.9733 0.00918 0.00372 -0.0988 0.2812 1.0000
4.750 0.9947 0.00940 0.00388 -0.0974 0.2718 1.0000
5.000 1.0161 0.00961 0.00404 -0.0961 0.2631 1.0000
5.250 1.0377 0.00982 0.00421 -0.0948 0.2557 1.0000
5.500 1.0591 0.01002 0.00438 -0.0935 0.2487 1.0000
5.750 1.0799 0.01025 0.00456 -0.0921 0.2415 1.0000
6.000 1.1016 0.01043 0.00473 -0.0908 0.2365 1.0000
6.250 1.1216 0.01066 0.00492 -0.0893 0.2309 1.0000
6.500 1.1406 0.01087 0.00512 -0.0875 0.2258 1.0000
6.750 1.1601 0.01106 0.00530 -0.0858 0.2205 1.0000
7.000 1.1782 0.01132 0.00552 -0.0840 0.2145 1.0000
7.250 1.1974 0.01154 0.00573 -0.0823 0.2094 1.0000
7.500 1.2166 0.01178 0.00594 -0.0807 0.2032 1.0000
7.750 1.2345 0.01208 0.00621 -0.0789 0.1972 1.0000
8.000 1.2547 0.01229 0.00643 -0.0775 0.1929 1.0000
8.250 1.2734 0.01258 0.00669 -0.0759 0.1866 1.0000
8.500 1.2914 0.01290 0.00699 -0.0742 0.1795 1.0000
8.750 1.3086 0.01326 0.00730 -0.0724 0.1703 1.0000
9.000 1.3241 0.01371 0.00768 -0.0705 0.1571 1.0000
9.250 1.3309 0.01457 0.00834 -0.0673 0.1289 1.0000
9.500 1.3258 0.01607 0.00956 -0.0625 0.0849 1.0000
9.750 1.3305 0.01719 0.01055 -0.0594 0.0657 1.0000
10.000 1.3436 0.01788 0.01123 -0.0575 0.0604 1.0000
10.250 1.3577 0.01855 0.01189 -0.0558 0.0576 1.0000
10.500 1.3713 0.01927 0.01262 -0.0541 0.0548 1.0000
10.750 1.3864 0.01992 0.01329 -0.0527 0.0528 1.0000
11.000 1.4020 0.02056 0.01395 -0.0514 0.0512 1.0000
11.250 1.4161 0.02132 0.01472 -0.0500 0.0493 1.0000
11.500 1.4279 0.02224 0.01565 -0.0485 0.0466 1.0000
11.750 1.4430 0.02298 0.01641 -0.0473 0.0447 1.0000
12.000 1.4570 0.02380 0.01725 -0.0462 0.0421 1.0000
12.250 1.4679 0.02487 0.01830 -0.0448 0.0377 1.0000
12.500 1.4668 0.02687 0.02015 -0.0426 0.0181 1.0000
12.750 1.4705 0.02860 0.02192 -0.0409 0.0148 1.0000
13.000 1.4782 0.03004 0.02343 -0.0397 0.0140 1.0000
13.250 1.4845 0.03166 0.02511 -0.0384 0.0131 1.0000
13.500 1.4920 0.03323 0.02674 -0.0374 0.0126 1.0000
13.750 1.4989 0.03487 0.02845 -0.0364 0.0122 1.0000
14.000 1.5050 0.03664 0.03028 -0.0355 0.0119 1.0000
14.250 1.5094 0.03861 0.03234 -0.0346 0.0116 1.0000
14.500 1.5125 0.04077 0.03457 -0.0338 0.0113 1.0000
14.750 1.5113 0.04341 0.03729 -0.0331 0.0110 1.0000
15.000 1.5105 0.04610 0.04007 -0.0324 0.0108 1.0000
15.250 1.5079 0.04907 0.04314 -0.0320 0.0106 1.0000
15.500 1.5098 0.05162 0.04575 -0.0317 0.0104 1.0000
15.750 1.5098 0.05440 0.04862 -0.0315 0.0103 1.0000
16.000 1.5076 0.05753 0.05183 -0.0314 0.0102 1.0000
16.250 1.5036 0.06095 0.05535 -0.0314 0.0101 1.0000
16.500 1.4992 0.06448 0.05897 -0.0316 0.0099 1.0000
16.750 1.4936 0.06822 0.06280 -0.0319 0.0098 1.0000
17.000 1.4849 0.07245 0.06714 -0.0324 0.0096 1.0000
17.250 1.4760 0.07682 0.07160 -0.0331 0.0096 1.0000
17.500 1.4653 0.08151 0.07640 -0.0340 0.0094 1.0000
17.750 1.4530 0.08650 0.08150 -0.0350 0.0094 1.0000
18.000 1.4396 0.09176 0.08687 -0.0363 0.0093 1.0000
18.250 1.4258 0.09719 0.09240 -0.0377 0.0093 1.0000
18.500 1.4103 0.10292 0.09825 -0.0394 0.0092 1.0000
18.750 1.3947 0.10881 0.10424 -0.0413 0.0091 1.0000
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