GOE 775 AIRFOIL (goe775-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 775 AIRFOIL (goe775-il) Reynolds number: 200,000 Max Cl/Cd: 48.4 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe775-il-200000.txt Download as CSV file: xf-goe775-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 775 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2044 0.09154 0.08507 -0.0477 1.0000 0.0858
-19.500 -1.1800 0.09191 0.08559 -0.0469 1.0000 0.0873
-19.250 -1.1766 0.08928 0.08294 -0.0478 1.0000 0.0888
-19.000 -1.1859 0.08492 0.07845 -0.0495 1.0000 0.0902
-18.750 -1.2024 0.07968 0.07300 -0.0516 1.0000 0.0917
-18.500 -1.2226 0.07421 0.06726 -0.0537 1.0000 0.0930
-18.250 -1.2072 0.07322 0.06636 -0.0533 1.0000 0.0948
-18.000 -1.1981 0.07148 0.06466 -0.0536 1.0000 0.0966
-17.750 -1.1995 0.06846 0.06155 -0.0543 1.0000 0.0985
-17.500 -1.2078 0.06472 0.05763 -0.0552 1.0000 0.1003
-17.250 -1.2165 0.06108 0.05378 -0.0559 1.0000 0.1020
-17.000 -1.1981 0.06038 0.05323 -0.0554 1.0000 0.1042
-16.750 -1.1929 0.05832 0.05115 -0.0556 1.0000 0.1064
-16.500 -1.1947 0.05555 0.04825 -0.0558 1.0000 0.1088
-16.250 -1.2033 0.05229 0.04475 -0.0561 1.0000 0.1108
-16.000 -1.1846 0.05153 0.04416 -0.0555 1.0000 0.1135
-15.750 -1.1788 0.04969 0.04231 -0.0553 1.0000 0.1161
-15.500 -1.1779 0.04744 0.03993 -0.0551 1.0000 0.1188
-15.250 -1.1737 0.04549 0.03789 -0.0546 1.0000 0.1215
-15.000 -1.1626 0.04419 0.03667 -0.0541 1.0000 0.1243
-14.750 -1.1570 0.04250 0.03494 -0.0536 1.0000 0.1274
-14.500 -1.1556 0.04056 0.03284 -0.0528 1.0000 0.1304
-14.250 -1.1434 0.03934 0.03170 -0.0521 1.0000 0.1337
-14.000 -1.1356 0.03796 0.03032 -0.0513 1.0000 0.1370
-13.750 -1.1305 0.03646 0.02872 -0.0503 1.0000 0.1405
-13.500 -1.1213 0.03517 0.02742 -0.0492 1.0000 0.1441
-13.250 -1.1121 0.03401 0.02631 -0.0481 1.0000 0.1476
-13.000 -1.1051 0.03282 0.02505 -0.0467 1.0000 0.1515
-12.750 -1.0971 0.03167 0.02385 -0.0453 1.0000 0.1555
-12.500 -1.0875 0.03069 0.02294 -0.0438 1.0000 0.1594
-12.250 -1.0803 0.02974 0.02195 -0.0419 1.0000 0.1637
-12.000 -1.0732 0.02881 0.02096 -0.0398 1.0000 0.1680
-11.750 -1.0650 0.02800 0.02023 -0.0377 1.0000 0.1722
-11.500 -1.0602 0.02727 0.01947 -0.0349 1.0000 0.1768
-11.250 -1.0565 0.02658 0.01872 -0.0318 1.0000 0.1814
-11.000 -1.0522 0.02593 0.01817 -0.0286 1.0000 0.1859
-10.750 -1.0522 0.02542 0.01764 -0.0246 1.0000 0.1906
-10.500 -1.0547 0.02498 0.01712 -0.0199 1.0000 0.1953
-10.250 -1.0558 0.02446 0.01671 -0.0155 1.0000 0.1998
-10.000 -1.0621 0.02413 0.01637 -0.0099 1.0000 0.2045
-9.750 -1.0708 0.02388 0.01604 -0.0038 1.0000 0.2091
-9.500 -1.0757 0.02347 0.01572 0.0016 1.0000 0.2139
-9.250 -1.0774 0.02314 0.01541 0.0065 1.0000 0.2195
-8.750 -1.0721 0.02240 0.01471 0.0146 1.0000 0.2322
-8.500 -1.0673 0.02213 0.01440 0.0183 1.0000 0.2394
-8.250 -1.0473 0.02170 0.01405 0.0190 0.9979 0.2482
-8.000 -1.0085 0.02139 0.01369 0.0162 0.9930 0.2601
-7.750 -0.9724 0.02096 0.01337 0.0140 0.9875 0.2713
-7.500 -0.9346 0.02057 0.01303 0.0115 0.9817 0.2828
-7.250 -0.8916 0.02031 0.01271 0.0080 0.9775 0.2953
-7.000 -0.8600 0.01986 0.01239 0.0069 0.9691 0.3059
-6.750 -0.8178 0.01948 0.01203 0.0037 0.9642 0.3181
-6.500 -0.7837 0.01917 0.01173 0.0022 0.9564 0.3298
-6.250 -0.7443 0.01875 0.01141 -0.0003 0.9502 0.3416
-6.000 -0.6990 0.01838 0.01103 -0.0039 0.9466 0.3549
-5.750 -0.6685 0.01805 0.01076 -0.0044 0.9369 0.3664
-5.500 -0.6257 0.01762 0.01040 -0.0075 0.9321 0.3793
-5.250 -0.5822 0.01723 0.00999 -0.0105 0.9285 0.3933
-5.000 -0.5557 0.01690 0.00976 -0.0101 0.9172 0.4045
-4.750 -0.5181 0.01648 0.00938 -0.0118 0.9114 0.4176
-4.500 -0.4904 0.01622 0.00912 -0.0116 0.9013 0.4306
-4.250 -0.4593 0.01585 0.00885 -0.0119 0.8925 0.4435
-4.000 -0.4318 0.01558 0.00858 -0.0115 0.8825 0.4571
-3.750 -0.4046 0.01530 0.00834 -0.0110 0.8716 0.4701
-3.500 -0.3783 0.01503 0.00813 -0.0103 0.8602 0.4817
-3.250 -0.3513 0.01479 0.00784 -0.0097 0.8491 0.4947
-3.000 -0.3259 0.01456 0.00770 -0.0089 0.8359 0.5059
-2.750 -0.2978 0.01432 0.00740 -0.0085 0.8254 0.5188
-2.500 -0.2734 0.01415 0.00730 -0.0075 0.8105 0.5305
-2.250 -0.2468 0.01397 0.00710 -0.0069 0.7979 0.5430
-2.000 -0.2201 0.01382 0.00694 -0.0062 0.7848 0.5556
-1.750 -0.1944 0.01370 0.00684 -0.0055 0.7704 0.5676
-1.500 -0.1680 0.01363 0.00669 -0.0048 0.7575 0.5813
-1.250 -0.1415 0.01353 0.00664 -0.0042 0.7432 0.5931
-1.000 -0.1163 0.01351 0.00657 -0.0034 0.7290 0.6066
-0.750 -0.0887 0.01348 0.00651 -0.0030 0.7163 0.6193
-0.500 -0.0641 0.01345 0.00651 -0.0020 0.7012 0.6323
-0.250 -0.0387 0.01347 0.00649 -0.0013 0.6878 0.6463
0.000 -0.0120 0.01345 0.00648 -0.0007 0.6741 0.6591
0.250 0.0121 0.01345 0.00648 0.0003 0.6598 0.6735
0.500 0.0391 0.01347 0.00649 0.0009 0.6471 0.6871
0.750 0.0642 0.01345 0.00651 0.0017 0.6330 0.7007
1.000 0.0890 0.01348 0.00652 0.0026 0.6202 0.7157
1.250 0.1165 0.01350 0.00657 0.0030 0.6073 0.7285
1.500 0.1417 0.01353 0.00664 0.0038 0.5940 0.7428
1.750 0.1684 0.01363 0.00668 0.0044 0.5822 0.7571
2.000 0.1946 0.01369 0.00684 0.0051 0.5684 0.7700
2.250 0.2204 0.01382 0.00693 0.0058 0.5566 0.7846
2.500 0.2469 0.01396 0.00710 0.0065 0.5439 0.7977
2.750 0.2737 0.01414 0.00730 0.0071 0.5315 0.8104
3.000 0.2979 0.01431 0.00740 0.0081 0.5197 0.8253
3.250 0.3262 0.01455 0.00769 0.0085 0.5070 0.8358
3.500 0.3517 0.01479 0.00783 0.0093 0.4959 0.8490
3.750 0.3785 0.01502 0.00812 0.0099 0.4828 0.8602
4.000 0.4049 0.01530 0.00833 0.0106 0.4713 0.8716
4.250 0.4319 0.01556 0.00858 0.0111 0.4582 0.8826
4.500 0.4597 0.01584 0.00884 0.0115 0.4448 0.8925
4.750 0.4907 0.01622 0.00910 0.0111 0.4319 0.9014
5.000 0.5185 0.01647 0.00938 0.0114 0.4188 0.9114
5.250 0.5561 0.01689 0.00975 0.0097 0.4058 0.9173
5.500 0.5827 0.01720 0.00998 0.0101 0.3944 0.9285
5.750 0.6262 0.01760 0.01039 0.0070 0.3805 0.9322
6.000 0.6690 0.01804 0.01074 0.0040 0.3677 0.9370
6.250 0.6997 0.01835 0.01102 0.0034 0.3560 0.9467
6.500 0.7450 0.01873 0.01139 -0.0003 0.3428 0.9503
6.750 0.7841 0.01915 0.01170 -0.0027 0.3311 0.9566
7.000 0.8186 0.01945 0.01201 -0.0043 0.3192 0.9643
7.250 0.8607 0.01984 0.01236 -0.0074 0.3071 0.9693
7.500 0.8927 0.02025 0.01268 -0.0087 0.2964 0.9777
7.750 0.9356 0.02053 0.01300 -0.0121 0.2839 0.9818
8.000 0.9732 0.02094 0.01333 -0.0146 0.2725 0.9878
8.250 1.0096 0.02132 0.01365 -0.0169 0.2612 0.9932
8.500 1.0484 0.02166 0.01402 -0.0197 0.2493 0.9981
8.750 1.0673 0.02210 0.01435 -0.0188 0.2407 1.0000
9.000 1.0722 0.02236 0.01467 -0.0151 0.2334 1.0000
9.250 1.0757 0.02277 0.01498 -0.0112 0.2271 1.0000
9.500 1.0777 0.02310 0.01536 -0.0070 0.2206 1.0000
9.750 1.0762 0.02342 0.01568 -0.0022 0.2149 1.0000
10.000 1.0721 0.02386 0.01599 0.0031 0.2101 1.0000
10.250 1.0628 0.02409 0.01632 0.0094 0.2055 1.0000
10.500 1.0565 0.02441 0.01667 0.0149 0.2008 1.0000
10.750 1.0541 0.02488 0.01705 0.0196 0.1963 1.0000
11.000 1.0531 0.02537 0.01757 0.0240 0.1916 1.0000
11.250 1.0532 0.02587 0.01811 0.0280 0.1868 1.0000
11.500 1.0568 0.02650 0.01866 0.0313 0.1823 1.0000
11.750 1.0615 0.02721 0.01939 0.0343 0.1777 1.0000
12.000 1.0664 0.02793 0.02016 0.0370 0.1730 1.0000
12.250 1.0741 0.02874 0.02090 0.0392 0.1688 1.0000
12.500 1.0822 0.02966 0.02185 0.0412 0.1644 1.0000
12.750 1.0893 0.03062 0.02286 0.0431 0.1601 1.0000
13.000 1.0984 0.03160 0.02380 0.0446 0.1562 1.0000
13.250 1.1076 0.03271 0.02493 0.0460 0.1522 1.0000
13.500 1.1144 0.03392 0.02621 0.0473 0.1483 1.0000
13.750 1.1231 0.03509 0.02736 0.0485 0.1447 1.0000
14.000 1.1337 0.03631 0.02854 0.0495 0.1412 1.0000
14.250 1.1385 0.03783 0.03019 0.0505 0.1377 1.0000
14.500 1.1460 0.03923 0.03159 0.0513 0.1343 1.0000
14.750 1.1602 0.04032 0.03256 0.0520 0.1310 1.0000
15.000 1.1606 0.04232 0.03474 0.0527 0.1280 1.0000
15.250 1.1657 0.04405 0.03654 0.0533 0.1249 1.0000
15.500 1.1750 0.04548 0.03791 0.0537 0.1221 1.0000
15.750 1.1827 0.04716 0.03962 0.0542 0.1193 1.0000
16.000 1.1825 0.04949 0.04209 0.0545 0.1167 1.0000
16.250 1.1875 0.05142 0.04405 0.0546 0.1140 1.0000
16.500 1.2018 0.05252 0.04505 0.0550 0.1115 1.0000
16.750 1.1998 0.05523 0.04790 0.0550 0.1092 1.0000
17.000 1.1970 0.05808 0.05090 0.0547 0.1069 1.0000
17.250 1.2010 0.06028 0.05313 0.0545 0.1047 1.0000
17.500 1.2161 0.06131 0.05405 0.0548 0.1025 1.0000
17.750 1.2136 0.06430 0.05718 0.0544 0.1006 1.0000
18.000 1.2045 0.06813 0.06121 0.0534 0.0988 1.0000
18.250 1.2021 0.07127 0.06444 0.0527 0.0969 1.0000
18.500 1.2096 0.07321 0.06636 0.0523 0.0951 1.0000
18.750 1.2288 0.07374 0.06676 0.0529 0.0932 1.0000
19.000 1.2082 0.07924 0.07253 0.0508 0.0919 1.0000
19.250 1.1915 0.08450 0.07801 0.0487 0.0904 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 775 AIRFOIL (goe775-il)