GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Reynolds number: 500,000 Max Cl/Cd: 92.59 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe256-il-500000.txt Download as CSV file: xf-goe256-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 256 (JUNKERS E) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1679 0.09959 0.09698 -0.0855 0.9395 0.0468
-10.750 -0.4962 0.03715 0.03338 -0.1203 0.8983 0.0404
-10.500 -0.4995 0.03420 0.03014 -0.1183 0.8894 0.0406
-10.250 -0.4888 0.03266 0.02846 -0.1170 0.8816 0.0409
-10.000 -0.4743 0.03147 0.02714 -0.1159 0.8745 0.0412
-9.750 -0.4572 0.03048 0.02604 -0.1149 0.8685 0.0415
-9.500 -0.4441 0.02882 0.02418 -0.1136 0.8615 0.0419
-9.250 -0.4315 0.02690 0.02200 -0.1122 0.8553 0.0424
-9.000 -0.4172 0.02507 0.01987 -0.1108 0.8496 0.0430
-8.750 -0.4003 0.02354 0.01809 -0.1095 0.8436 0.0438
-8.500 -0.3818 0.02215 0.01639 -0.1084 0.8385 0.0445
-8.250 -0.3608 0.02108 0.01502 -0.1075 0.8342 0.0451
-8.000 -0.3401 0.01969 0.01346 -0.1067 0.8294 0.0457
-7.750 -0.3160 0.01895 0.01269 -0.1062 0.8247 0.0463
-7.500 -0.2908 0.01848 0.01217 -0.1059 0.8205 0.0469
-7.250 -0.2651 0.01805 0.01164 -0.1056 0.8167 0.0477
-7.000 -0.2399 0.01755 0.01107 -0.1052 0.8128 0.0485
-6.750 -0.2145 0.01701 0.01045 -0.1049 0.8086 0.0495
-6.500 -0.1887 0.01657 0.00987 -0.1045 0.8038 0.0505
-6.250 -0.1631 0.01592 0.00907 -0.1041 0.7982 0.0516
-6.000 -0.1380 0.01541 0.00858 -0.1036 0.7914 0.0526
-5.750 -0.1116 0.01510 0.00823 -0.1033 0.7859 0.0537
-5.500 -0.0844 0.01482 0.00787 -0.1032 0.7819 0.0550
-5.250 -0.0580 0.01450 0.00751 -0.1029 0.7779 0.0564
-5.000 -0.0311 0.01427 0.00721 -0.1026 0.7736 0.0576
-4.750 -0.0053 0.01368 0.00662 -0.1024 0.7696 0.0594
-4.500 0.0222 0.01352 0.00644 -0.1023 0.7657 0.0611
-4.250 0.0493 0.01335 0.00624 -0.1021 0.7618 0.0631
-4.000 0.0764 0.01319 0.00604 -0.1019 0.7575 0.0649
-3.750 0.1021 0.01270 0.00556 -0.1016 0.7533 0.0671
-3.500 0.1294 0.01251 0.00536 -0.1014 0.7492 0.0692
-3.250 0.1569 0.01239 0.00520 -0.1013 0.7452 0.0717
-3.000 0.1840 0.01231 0.00510 -0.1011 0.7408 0.0738
-2.750 0.2092 0.01186 0.00469 -0.1007 0.7362 0.0770
-2.500 0.2365 0.01171 0.00452 -0.1005 0.7320 0.0797
-2.250 0.2641 0.01162 0.00439 -0.1004 0.7277 0.0826
-2.000 0.2896 0.01135 0.00415 -0.0999 0.7227 0.0858
-1.750 0.3159 0.01115 0.00397 -0.0996 0.7177 0.0893
-1.500 0.3433 0.01105 0.00383 -0.0995 0.7131 0.0930
-1.250 0.3699 0.01091 0.00369 -0.0992 0.7082 0.0968
-1.000 0.3957 0.01072 0.00355 -0.0988 0.7024 0.1020
-0.750 0.4227 0.01063 0.00343 -0.0985 0.6967 0.1071
-0.500 0.4490 0.01048 0.00331 -0.0982 0.6910 0.1152
-0.250 0.4748 0.01033 0.00322 -0.0978 0.6844 0.1279
0.000 0.4997 0.01002 0.00311 -0.0973 0.6782 0.1845
0.250 0.5188 0.00924 0.00311 -0.0959 0.6715 0.4243
0.500 0.5327 0.00839 0.00309 -0.0932 0.6638 0.6730
0.750 0.5568 0.00817 0.00355 -0.0912 0.6560 0.9318
1.000 0.5883 0.00837 0.00372 -0.0915 0.6456 0.9558
1.250 0.6407 0.00863 0.00390 -0.0965 0.6337 0.9695
1.500 0.6980 0.00885 0.00403 -0.1027 0.6192 0.9804
1.750 0.7635 0.00900 0.00405 -0.1108 0.5996 0.9881
2.000 0.8288 0.00914 0.00401 -0.1190 0.5755 0.9976
2.250 0.8629 0.00932 0.00404 -0.1206 0.5534 1.0000
2.500 0.8831 0.00955 0.00414 -0.1192 0.5344 1.0000
2.750 0.9029 0.00978 0.00426 -0.1177 0.5181 1.0000
3.000 0.9224 0.01003 0.00440 -0.1162 0.5042 1.0000
3.250 0.9420 0.01025 0.00455 -0.1147 0.4919 1.0000
3.500 0.9619 0.01045 0.00469 -0.1133 0.4816 1.0000
4.000 1.0000 0.01087 0.00501 -0.1100 0.4636 1.0000
4.250 1.0174 0.01112 0.00519 -0.1081 0.4557 1.0000
4.500 1.0361 0.01129 0.00535 -0.1064 0.4486 1.0000
4.750 1.0526 0.01152 0.00553 -0.1043 0.4407 1.0000
5.000 1.0684 0.01173 0.00571 -0.1020 0.4329 1.0000
5.250 1.0833 0.01193 0.00588 -0.0996 0.4250 1.0000
5.500 1.0959 0.01220 0.00609 -0.0967 0.4187 1.0000
5.750 1.1111 0.01234 0.00626 -0.0943 0.4134 1.0000
6.000 1.1220 0.01253 0.00644 -0.0910 0.4079 1.0000
6.250 1.1258 0.01276 0.00662 -0.0863 0.4028 1.0000
6.500 1.1348 0.01289 0.00678 -0.0827 0.3984 1.0000
6.750 1.1451 0.01305 0.00696 -0.0794 0.3939 1.0000
7.000 1.1560 0.01328 0.00717 -0.0762 0.3895 1.0000
7.250 1.1678 0.01360 0.00744 -0.0734 0.3848 1.0000
7.500 1.1845 0.01378 0.00768 -0.0715 0.3804 1.0000
7.750 1.2014 0.01404 0.00795 -0.0698 0.3752 1.0000
8.000 1.2178 0.01439 0.00827 -0.0680 0.3704 1.0000
8.250 1.2362 0.01472 0.00861 -0.0667 0.3663 1.0000
8.500 1.2560 0.01499 0.00894 -0.0656 0.3620 1.0000
8.750 1.2743 0.01534 0.00930 -0.0643 0.3570 1.0000
9.000 1.2916 0.01578 0.00971 -0.0630 0.3523 1.0000
9.250 1.3109 0.01614 0.01011 -0.0619 0.3481 1.0000
9.500 1.3302 0.01650 0.01053 -0.0610 0.3432 1.0000
9.750 1.3476 0.01696 0.01099 -0.0597 0.3382 1.0000
10.000 1.3644 0.01748 0.01151 -0.0585 0.3332 1.0000
10.250 1.3832 0.01789 0.01200 -0.0576 0.3270 1.0000
10.500 1.3975 0.01853 0.01261 -0.0561 0.3197 1.0000
10.750 1.4147 0.01907 0.01320 -0.0550 0.3123 1.0000
11.000 1.4291 0.01976 0.01389 -0.0537 0.3044 1.0000
11.250 1.4449 0.02041 0.01457 -0.0526 0.2963 1.0000
11.500 1.4574 0.02126 0.01541 -0.0511 0.2870 1.0000
11.750 1.4713 0.02205 0.01623 -0.0499 0.2756 1.0000
12.000 1.4819 0.02308 0.01722 -0.0484 0.2617 1.0000
12.250 1.4894 0.02433 0.01843 -0.0467 0.2445 1.0000
12.500 1.4921 0.02596 0.01996 -0.0446 0.2233 1.0000
12.750 1.4906 0.02793 0.02180 -0.0423 0.1984 1.0000
13.000 1.4882 0.03008 0.02384 -0.0400 0.1803 1.0000
13.250 1.4881 0.03212 0.02582 -0.0381 0.1681 1.0000
13.500 1.4922 0.03390 0.02760 -0.0367 0.1597 1.0000
13.750 1.4939 0.03592 0.02962 -0.0352 0.1529 1.0000
14.000 1.5011 0.03755 0.03129 -0.0341 0.1476 1.0000
14.250 1.5042 0.03954 0.03331 -0.0329 0.1426 1.0000
14.500 1.5085 0.04149 0.03529 -0.0319 0.1382 1.0000
14.750 1.5151 0.04328 0.03713 -0.0311 0.1336 1.0000
15.000 1.5171 0.04553 0.03942 -0.0301 0.1290 1.0000
15.250 1.5204 0.04769 0.04163 -0.0293 0.1248 1.0000
15.500 1.5257 0.04971 0.04370 -0.0287 0.1203 1.0000
15.750 1.5255 0.05233 0.04634 -0.0279 0.1157 1.0000
16.000 1.5285 0.05467 0.04874 -0.0274 0.1108 1.0000
16.250 1.5288 0.05737 0.05148 -0.0269 0.1053 1.0000
16.500 1.5271 0.06031 0.05447 -0.0265 0.0995 1.0000
16.750 1.5205 0.06389 0.05804 -0.0262 0.0912 1.0000
17.000 1.5125 0.06773 0.06188 -0.0260 0.0795 1.0000
17.250 1.4944 0.07286 0.06694 -0.0259 0.0631 1.0000
17.500 1.4694 0.07896 0.07296 -0.0260 0.0471 1.0000
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