GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 619 AIRFOIL (goe619-il) Reynolds number: 200,000 Max Cl/Cd: 67.57 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe619-il-200000-n5.txt Download as CSV file: xf-goe619-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6232 0.06292 0.05861 -0.0752 1.0000 0.0364
-12.000 -0.6794 0.05360 0.04917 -0.0803 1.0000 0.0361
-11.750 -0.7267 0.04650 0.04196 -0.0847 0.9992 0.0360
-11.500 -0.7247 0.03987 0.03488 -0.0953 0.9873 0.0362
-11.250 -0.7103 0.03638 0.03104 -0.0994 0.9791 0.0366
-11.000 -0.6909 0.03379 0.02812 -0.1022 0.9722 0.0370
-10.750 -0.6726 0.03177 0.02598 -0.1031 0.9646 0.0377
-10.500 -0.6472 0.03015 0.02428 -0.1047 0.9595 0.0383
-10.250 -0.6249 0.02876 0.02278 -0.1053 0.9526 0.0388
-10.000 -0.5993 0.02739 0.02127 -0.1064 0.9469 0.0394
-9.750 -0.5693 0.02603 0.01975 -0.1081 0.9434 0.0400
-9.500 -0.5476 0.02492 0.01851 -0.1079 0.9348 0.0406
-9.250 -0.5172 0.02377 0.01721 -0.1093 0.9304 0.0413
-9.000 -0.4885 0.02276 0.01604 -0.1103 0.9250 0.0421
-8.750 -0.4616 0.02187 0.01499 -0.1106 0.9179 0.0430
-8.500 -0.4298 0.02089 0.01392 -0.1120 0.9133 0.0440
-8.250 -0.4032 0.02010 0.01308 -0.1123 0.9059 0.0449
-8.000 -0.3736 0.01937 0.01226 -0.1130 0.8996 0.0460
-7.750 -0.3406 0.01865 0.01144 -0.1143 0.8948 0.0472
-7.500 -0.3154 0.01809 0.01079 -0.1140 0.8858 0.0485
-7.250 -0.2837 0.01749 0.01007 -0.1149 0.8798 0.0501
-7.000 -0.2578 0.01697 0.00951 -0.1146 0.8714 0.0519
-6.750 -0.2284 0.01649 0.00898 -0.1150 0.8644 0.0549
-6.500 -0.2008 0.01607 0.00851 -0.1150 0.8568 0.0590
-6.250 -0.1730 0.01571 0.00812 -0.1150 0.8487 0.0652
-6.000 -0.1446 0.01540 0.00777 -0.1150 0.8415 0.0729
-5.750 -0.1178 0.01514 0.00746 -0.1147 0.8334 0.0807
-5.500 -0.0883 0.01493 0.00713 -0.1149 0.8267 0.0882
-5.250 -0.0630 0.01470 0.00687 -0.1143 0.8180 0.0941
-5.000 -0.0341 0.01451 0.00657 -0.1143 0.8113 0.1001
-4.750 -0.0084 0.01432 0.00633 -0.1138 0.8031 0.1049
-4.500 0.0190 0.01410 0.00607 -0.1136 0.7959 0.1113
-4.250 0.0456 0.01396 0.00585 -0.1132 0.7884 0.1172
-4.000 0.0721 0.01374 0.00562 -0.1128 0.7809 0.1230
-3.750 0.0992 0.01357 0.00541 -0.1125 0.7741 0.1297
-3.500 0.1252 0.01340 0.00523 -0.1120 0.7662 0.1364
-3.250 0.1530 0.01324 0.00503 -0.1119 0.7599 0.1456
-3.000 0.1782 0.01308 0.00493 -0.1112 0.7517 0.1569
-2.750 0.2055 0.01294 0.00479 -0.1110 0.7448 0.1721
-2.500 0.2314 0.01283 0.00472 -0.1104 0.7369 0.1890
-2.250 0.2582 0.01275 0.00462 -0.1100 0.7293 0.2069
-2.000 0.2844 0.01269 0.00456 -0.1095 0.7210 0.2238
-1.750 0.3110 0.01263 0.00447 -0.1090 0.7118 0.2394
-1.500 0.3364 0.01258 0.00441 -0.1083 0.7009 0.2527
-1.250 0.3623 0.01255 0.00431 -0.1076 0.6889 0.2649
-1.000 0.3880 0.01253 0.00423 -0.1069 0.6772 0.2768
-0.750 0.4132 0.01249 0.00420 -0.1062 0.6662 0.2877
-0.500 0.4394 0.01249 0.00415 -0.1056 0.6576 0.2994
-0.250 0.4650 0.01248 0.00415 -0.1050 0.6486 0.3120
0.000 0.4908 0.01247 0.00415 -0.1044 0.6402 0.3258
0.250 0.5161 0.01245 0.00416 -0.1037 0.6306 0.3405
0.500 0.5415 0.01245 0.00418 -0.1030 0.6216 0.3567
0.750 0.5666 0.01244 0.00421 -0.1023 0.6122 0.3762
1.000 0.5915 0.01244 0.00426 -0.1016 0.6029 0.3979
1.500 0.6403 0.01243 0.00435 -0.0999 0.5814 0.4441
1.750 0.6642 0.01243 0.00439 -0.0989 0.5693 0.4702
2.000 0.6872 0.01240 0.00443 -0.0978 0.5564 0.5021
2.250 0.7087 0.01231 0.00448 -0.0965 0.5422 0.5520
2.500 0.7712 0.01167 0.00473 -0.1032 0.5214 1.0000
2.750 0.7923 0.01186 0.00480 -0.1018 0.5040 1.0000
3.000 0.8129 0.01207 0.00489 -0.1002 0.4850 1.0000
3.250 0.8325 0.01232 0.00501 -0.0985 0.4647 1.0000
3.500 0.8512 0.01262 0.00515 -0.0966 0.4439 1.0000
3.750 0.8700 0.01293 0.00533 -0.0948 0.4228 1.0000
4.000 0.8882 0.01327 0.00554 -0.0929 0.4026 1.0000
4.250 0.9064 0.01363 0.00577 -0.0910 0.3845 1.0000
4.500 0.9246 0.01398 0.00602 -0.0892 0.3683 1.0000
4.750 0.9424 0.01436 0.00629 -0.0873 0.3527 1.0000
5.000 0.9600 0.01474 0.00658 -0.0854 0.3382 1.0000
5.250 0.9771 0.01514 0.00688 -0.0835 0.3248 1.0000
5.500 0.9931 0.01556 0.00720 -0.0814 0.3115 1.0000
5.750 1.0100 0.01592 0.00752 -0.0794 0.3008 1.0000
6.000 1.0262 0.01631 0.00784 -0.0773 0.2915 1.0000
6.250 1.0429 0.01669 0.00819 -0.0753 0.2837 1.0000
6.500 1.0598 0.01709 0.00856 -0.0734 0.2775 1.0000
6.750 1.0778 0.01745 0.00893 -0.0718 0.2711 1.0000
7.000 1.0945 0.01788 0.00933 -0.0699 0.2658 1.0000
7.250 1.1118 0.01830 0.00974 -0.0682 0.2607 1.0000
7.500 1.1299 0.01869 0.01016 -0.0667 0.2556 1.0000
7.750 1.1458 0.01917 0.01062 -0.0649 0.2499 1.0000
8.000 1.1621 0.01965 0.01110 -0.0632 0.2444 1.0000
8.250 1.1794 0.02010 0.01157 -0.0617 0.2388 1.0000
8.500 1.1951 0.02062 0.01211 -0.0600 0.2338 1.0000
8.750 1.2102 0.02119 0.01267 -0.0583 0.2301 1.0000
9.000 1.2283 0.02165 0.01320 -0.0570 0.2264 1.0000
9.250 1.2447 0.02218 0.01378 -0.0555 0.2219 1.0000
9.500 1.2580 0.02284 0.01445 -0.0537 0.2163 1.0000
9.750 1.2730 0.02345 0.01510 -0.0522 0.2103 1.0000
10.000 1.2866 0.02414 0.01581 -0.0506 0.2029 1.0000
10.250 1.2991 0.02490 0.01658 -0.0490 0.1958 1.0000
10.500 1.3128 0.02563 0.01736 -0.0475 0.1881 1.0000
10.750 1.3248 0.02649 0.01824 -0.0460 0.1806 1.0000
11.000 1.3357 0.02743 0.01919 -0.0444 0.1699 1.0000
11.250 1.3463 0.02844 0.02020 -0.0429 0.1571 1.0000
11.500 1.3531 0.02974 0.02145 -0.0413 0.1397 1.0000
11.750 1.3567 0.03134 0.02295 -0.0395 0.1204 1.0000
12.000 1.3528 0.03361 0.02506 -0.0375 0.0954 1.0000
12.250 1.3511 0.03582 0.02718 -0.0358 0.0808 1.0000
12.500 1.3531 0.03781 0.02917 -0.0344 0.0737 1.0000
12.750 1.3558 0.03979 0.03118 -0.0332 0.0692 1.0000
13.000 1.3594 0.04175 0.03320 -0.0322 0.0661 1.0000
13.250 1.3614 0.04393 0.03544 -0.0313 0.0631 1.0000
13.500 1.3623 0.04630 0.03787 -0.0305 0.0604 1.0000
13.750 1.3662 0.04843 0.04011 -0.0299 0.0585 1.0000
14.000 1.3683 0.05081 0.04258 -0.0295 0.0563 1.0000
14.250 1.3678 0.05355 0.04540 -0.0291 0.0542 1.0000
14.500 1.3673 0.05639 0.04833 -0.0289 0.0528 1.0000
14.750 1.3646 0.05958 0.05161 -0.0289 0.0512 1.0000
15.000 1.3672 0.06222 0.05437 -0.0289 0.0497 1.0000
15.250 1.3679 0.06516 0.05744 -0.0291 0.0482 1.0000
15.500 1.3663 0.06847 0.06087 -0.0295 0.0462 1.0000
15.750 1.3601 0.07250 0.06499 -0.0302 0.0440 1.0000
16.000 1.3578 0.07610 0.06871 -0.0309 0.0420 1.0000
16.250 1.3558 0.07974 0.07247 -0.0317 0.0388 1.0000
16.500 1.3512 0.08385 0.07670 -0.0327 0.0341 1.0000
16.750 1.3345 0.08993 0.08280 -0.0347 0.0208 1.0000
17.000 1.3176 0.09623 0.08916 -0.0369 0.0195 1.0000
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