GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 527 AIRFOIL (goe527-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.92 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe527-il-1000000-n5.txt Download as CSV file: xf-goe527-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 527 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7317 0.07808 0.07543 -0.0840 1.0000 0.0223
-16.500 -0.8270 0.06167 0.05879 -0.0943 1.0000 0.0222
-16.000 -0.9293 0.03570 0.03228 -0.1187 0.9925 0.0222
-15.750 -0.9260 0.03092 0.02732 -0.1255 0.9817 0.0223
-15.500 -0.9089 0.02829 0.02454 -0.1300 0.9683 0.0224
-15.250 -0.8790 0.02567 0.02178 -0.1364 0.9538 0.0227
-15.000 -0.8350 0.02389 0.01988 -0.1431 0.9416 0.0231
-14.750 -0.7941 0.02256 0.01841 -0.1481 0.9221 0.0233
-14.500 -0.7743 0.02172 0.01742 -0.1484 0.8958 0.0235
-14.250 -0.7667 0.02110 0.01664 -0.1458 0.8720 0.0237
-14.000 -0.7618 0.02058 0.01598 -0.1425 0.8508 0.0238
-13.750 -0.7502 0.02009 0.01538 -0.1401 0.8355 0.0240
-13.500 -0.7359 0.01964 0.01482 -0.1382 0.8217 0.0243
-13.250 -0.7211 0.01917 0.01425 -0.1363 0.8081 0.0245
-13.000 -0.7057 0.01867 0.01364 -0.1345 0.7952 0.0247
-12.750 -0.6884 0.01822 0.01309 -0.1329 0.7836 0.0249
-12.500 -0.6709 0.01777 0.01252 -0.1313 0.7727 0.0251
-12.250 -0.6516 0.01733 0.01200 -0.1300 0.7629 0.0253
-12.000 -0.6317 0.01695 0.01152 -0.1287 0.7539 0.0255
-11.750 -0.6105 0.01659 0.01107 -0.1276 0.7450 0.0257
-11.500 -0.5894 0.01626 0.01064 -0.1264 0.7359 0.0258
-11.250 -0.5696 0.01574 0.01006 -0.1252 0.7274 0.0261
-11.000 -0.5491 0.01531 0.00955 -0.1239 0.7187 0.0264
-10.750 -0.5269 0.01491 0.00910 -0.1229 0.7118 0.0267
-10.500 -0.5042 0.01457 0.00870 -0.1220 0.7043 0.0269
-10.250 -0.4812 0.01426 0.00832 -0.1211 0.6974 0.0272
-10.000 -0.4574 0.01395 0.00796 -0.1203 0.6901 0.0274
-9.750 -0.4338 0.01368 0.00762 -0.1195 0.6820 0.0277
-9.500 -0.4093 0.01342 0.00730 -0.1187 0.6750 0.0281
-9.250 -0.3849 0.01316 0.00699 -0.1180 0.6673 0.0284
-9.000 -0.3604 0.01292 0.00668 -0.1173 0.6605 0.0287
-8.750 -0.3353 0.01267 0.00638 -0.1166 0.6538 0.0290
-8.500 -0.3104 0.01246 0.00610 -0.1160 0.6462 0.0293
-8.250 -0.2851 0.01225 0.00583 -0.1153 0.6394 0.0295
-8.000 -0.2603 0.01200 0.00552 -0.1146 0.6311 0.0298
-7.750 -0.2356 0.01176 0.00523 -0.1139 0.6235 0.0303
-7.500 -0.2101 0.01154 0.00498 -0.1133 0.6162 0.0307
-7.250 -0.1847 0.01136 0.00475 -0.1127 0.6087 0.0312
-7.000 -0.1588 0.01118 0.00453 -0.1122 0.6023 0.0317
-6.750 -0.1329 0.01103 0.00433 -0.1117 0.5946 0.0322
-6.500 -0.1071 0.01090 0.00414 -0.1111 0.5873 0.0327
-6.250 -0.0807 0.01076 0.00397 -0.1106 0.5804 0.0333
-6.000 -0.0548 0.01063 0.00379 -0.1101 0.5734 0.0339
-5.750 -0.0287 0.01047 0.00361 -0.1096 0.5680 0.0348
-5.500 -0.0022 0.01034 0.00346 -0.1091 0.5620 0.0357
-5.250 0.0238 0.01024 0.00331 -0.1086 0.5554 0.0367
-5.000 0.0504 0.01014 0.00318 -0.1082 0.5502 0.0378
-4.750 0.0770 0.01001 0.00305 -0.1078 0.5450 0.0394
-4.500 0.1035 0.00992 0.00293 -0.1073 0.5399 0.0414
-4.250 0.1296 0.00984 0.00283 -0.1069 0.5348 0.0442
-4.000 0.1566 0.00973 0.00273 -0.1065 0.5306 0.0480
-3.750 0.1832 0.00964 0.00265 -0.1061 0.5260 0.0535
-3.500 0.2098 0.00957 0.00259 -0.1057 0.5216 0.0593
-3.000 0.2635 0.00946 0.00249 -0.1050 0.5140 0.0687
-2.750 0.2906 0.00941 0.00245 -0.1047 0.5101 0.0730
-2.500 0.3175 0.00939 0.00241 -0.1044 0.5060 0.0760
-2.250 0.3441 0.00936 0.00238 -0.1040 0.5023 0.0797
-2.000 0.3708 0.00936 0.00236 -0.1036 0.4986 0.0830
-1.750 0.3982 0.00933 0.00233 -0.1034 0.4954 0.0857
-1.500 0.4250 0.00929 0.00231 -0.1031 0.4910 0.0897
-1.250 0.4514 0.00930 0.00230 -0.1026 0.4858 0.0929
-1.000 0.4776 0.00932 0.00229 -0.1022 0.4806 0.0957
-0.750 0.5045 0.00928 0.00227 -0.1019 0.4769 0.1012
-0.500 0.5312 0.00927 0.00227 -0.1016 0.4725 0.1060
-0.250 0.5572 0.00928 0.00226 -0.1011 0.4677 0.1108
0.000 0.5830 0.00928 0.00227 -0.1006 0.4628 0.1173
0.250 0.6095 0.00926 0.00227 -0.1003 0.4579 0.1266
0.500 0.6350 0.00922 0.00228 -0.0998 0.4525 0.1489
0.750 0.6594 0.00914 0.00232 -0.0991 0.4478 0.2010
1.000 0.6845 0.00906 0.00236 -0.0985 0.4442 0.2454
1.250 0.7099 0.00898 0.00240 -0.0980 0.4401 0.2882
1.500 0.7344 0.00891 0.00245 -0.0974 0.4353 0.3402
1.750 0.7578 0.00883 0.00253 -0.0966 0.4309 0.4078
2.000 0.7820 0.00877 0.00260 -0.0958 0.4273 0.4629
2.250 0.8062 0.00871 0.00268 -0.0951 0.4231 0.5190
2.500 0.8293 0.00869 0.00276 -0.0942 0.4168 0.5671
2.750 0.8506 0.00865 0.00286 -0.0929 0.4102 0.6327
3.000 0.8682 0.00845 0.00298 -0.0908 0.4032 0.7552
3.250 0.8936 0.00825 0.00323 -0.0901 0.3947 0.9436
3.500 0.9437 0.00844 0.00339 -0.0950 0.3867 0.9688
3.750 0.9961 0.00870 0.00358 -0.1005 0.3780 0.9836
4.000 1.0464 0.00895 0.00377 -0.1055 0.3689 0.9998
4.250 1.0651 0.00913 0.00390 -0.1037 0.3614 1.0000
4.500 1.0834 0.00929 0.00402 -0.1019 0.3536 1.0000
4.750 1.1000 0.00950 0.00418 -0.0997 0.3448 1.0000
5.000 1.1154 0.00969 0.00433 -0.0973 0.3355 1.0000
5.250 1.1287 0.00991 0.00450 -0.0944 0.3263 1.0000
5.500 1.1421 0.01016 0.00469 -0.0917 0.3161 1.0000
5.750 1.1577 0.01039 0.00488 -0.0894 0.3077 1.0000
6.000 1.1721 0.01069 0.00513 -0.0870 0.2978 1.0000
6.250 1.1871 0.01100 0.00539 -0.0848 0.2869 1.0000
6.500 1.2024 0.01133 0.00567 -0.0826 0.2774 1.0000
6.750 1.2173 0.01169 0.00598 -0.0805 0.2683 1.0000
7.000 1.2342 0.01200 0.00627 -0.0787 0.2615 1.0000
7.250 1.2506 0.01235 0.00659 -0.0770 0.2551 1.0000
7.500 1.2668 0.01272 0.00694 -0.0752 0.2493 1.0000
7.750 1.2843 0.01306 0.00727 -0.0737 0.2444 1.0000
8.000 1.3007 0.01346 0.00766 -0.0722 0.2392 1.0000
8.250 1.3165 0.01391 0.00809 -0.0705 0.2345 1.0000
8.500 1.3344 0.01429 0.00848 -0.0693 0.2314 1.0000
8.750 1.3510 0.01474 0.00893 -0.0679 0.2270 1.0000
9.000 1.3659 0.01530 0.00947 -0.0664 0.2219 1.0000
9.250 1.3812 0.01587 0.01003 -0.0650 0.2178 1.0000
9.500 1.3986 0.01635 0.01054 -0.0639 0.2151 1.0000
9.750 1.4154 0.01689 0.01109 -0.0629 0.2123 1.0000
10.000 1.4313 0.01750 0.01171 -0.0617 0.2094 1.0000
10.250 1.4457 0.01821 0.01243 -0.0605 0.2059 1.0000
10.500 1.4596 0.01898 0.01321 -0.0593 0.2026 1.0000
10.750 1.4762 0.01962 0.01388 -0.0585 0.2008 1.0000
11.000 1.4923 0.02031 0.01461 -0.0576 0.1988 1.0000
11.250 1.5072 0.02109 0.01541 -0.0567 0.1963 1.0000
11.500 1.5209 0.02196 0.01631 -0.0557 0.1934 1.0000
11.750 1.5327 0.02299 0.01735 -0.0547 0.1903 1.0000
12.000 1.5443 0.02406 0.01844 -0.0537 0.1870 1.0000
12.250 1.5581 0.02498 0.01941 -0.0529 0.1844 1.0000
12.500 1.5686 0.02618 0.02061 -0.0519 0.1793 1.0000
12.750 1.5747 0.02773 0.02215 -0.0507 0.1730 1.0000
13.000 1.5826 0.02918 0.02361 -0.0498 0.1653 1.0000
13.250 1.5839 0.03118 0.02558 -0.0485 0.1547 1.0000
13.500 1.5830 0.03342 0.02778 -0.0472 0.1443 1.0000
13.750 1.5837 0.03562 0.02997 -0.0461 0.1370 1.0000
14.000 1.5804 0.03820 0.03253 -0.0449 0.1284 1.0000
14.250 1.5790 0.04067 0.03501 -0.0439 0.1227 1.0000
14.500 1.5818 0.04284 0.03721 -0.0433 0.1193 1.0000
14.750 1.5853 0.04494 0.03935 -0.0426 0.1169 1.0000
15.000 1.5857 0.04739 0.04183 -0.0420 0.1139 1.0000
15.250 1.5880 0.04970 0.04418 -0.0415 0.1116 1.0000
15.500 1.5927 0.05178 0.04631 -0.0411 0.1099 1.0000
15.750 1.5960 0.05405 0.04863 -0.0408 0.1087 1.0000
16.000 1.5982 0.05640 0.05103 -0.0404 0.1069 1.0000
16.250 1.6000 0.05883 0.05351 -0.0401 0.1056 1.0000
16.500 1.6001 0.06149 0.05622 -0.0398 0.1039 1.0000
16.750 1.6001 0.06415 0.05893 -0.0396 0.1019 1.0000
17.000 1.6005 0.06682 0.06165 -0.0395 0.1003 1.0000
17.250 1.6048 0.06902 0.06392 -0.0393 0.0992 1.0000
17.500 1.6063 0.07158 0.06654 -0.0393 0.0979 1.0000
17.750 1.6076 0.07416 0.06917 -0.0392 0.0960 1.0000
18.000 1.6070 0.07699 0.07205 -0.0392 0.0945 1.0000
18.250 1.6041 0.08009 0.07518 -0.0393 0.0919 1.0000
18.500 1.6009 0.08324 0.07839 -0.0394 0.0897 1.0000
18.750 1.6029 0.08577 0.08098 -0.0395 0.0878 1.0000
19.000 1.6011 0.08880 0.08406 -0.0397 0.0848 1.0000
19.250 1.5944 0.09243 0.08769 -0.0400 0.0799 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 527 AIRFOIL (goe527-il)