GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 767 AIRFOIL (goe767-il) Reynolds number: 500,000 Max Cl/Cd: 76.02 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe767-il-500000.txt Download as CSV file: xf-goe767-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 767 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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0740 0.08575 0.08221 -0.0175 1.0000 0.0322
-16.250 -1.1159 0.07424 0.07046 -0.0262 1.0000 0.0321
-16.000 -1.1437 0.06579 0.06181 -0.0326 1.0000 0.0321
-15.750 -1.1670 0.05865 0.05447 -0.0380 1.0000 0.0321
-15.500 -1.1844 0.05308 0.04870 -0.0418 1.0000 0.0322
-15.250 -1.1976 0.04867 0.04411 -0.0442 1.0000 0.0322
-15.000 -1.2089 0.04504 0.04030 -0.0455 1.0000 0.0323
-14.750 -1.2179 0.04209 0.03718 -0.0456 1.0000 0.0324
-14.500 -1.2257 0.03893 0.03388 -0.0449 1.0000 0.0327
-14.250 -1.2267 0.03669 0.03156 -0.0436 1.0000 0.0329
-14.000 -1.2242 0.03498 0.02979 -0.0420 1.0000 0.0332
-13.750 -1.2208 0.03353 0.02829 -0.0401 1.0000 0.0335
-13.500 -1.2165 0.03228 0.02697 -0.0377 1.0000 0.0338
-13.250 -1.2109 0.03119 0.02581 -0.0352 1.0000 0.0341
-13.000 -1.2020 0.03008 0.02462 -0.0331 1.0000 0.0345
-12.750 -1.1905 0.02895 0.02338 -0.0313 1.0000 0.0349
-12.500 -1.1772 0.02785 0.02218 -0.0296 1.0000 0.0352
-12.250 -1.1625 0.02680 0.02102 -0.0280 1.0000 0.0356
-12.000 -1.1466 0.02581 0.01993 -0.0264 1.0000 0.0360
-11.750 -1.1294 0.02490 0.01890 -0.0250 1.0000 0.0363
-11.500 -1.1110 0.02411 0.01799 -0.0236 1.0000 0.0367
-11.250 -1.0948 0.02275 0.01658 -0.0222 1.0000 0.0372
-11.000 -1.0766 0.02177 0.01558 -0.0208 1.0000 0.0378
-10.750 -1.0568 0.02100 0.01480 -0.0196 1.0000 0.0384
-10.500 -1.0363 0.02028 0.01405 -0.0184 1.0000 0.0390
-10.250 -1.0154 0.01959 0.01331 -0.0172 1.0000 0.0396
-10.000 -0.9941 0.01893 0.01259 -0.0160 1.0000 0.0402
-9.750 -0.9723 0.01832 0.01191 -0.0149 1.0000 0.0408
-9.500 -0.9499 0.01776 0.01128 -0.0138 1.0000 0.0413
-9.250 -0.9296 0.01694 0.01045 -0.0124 1.0000 0.0421
-9.000 -0.9082 0.01627 0.00979 -0.0112 1.0000 0.0430
-8.750 -0.8857 0.01575 0.00926 -0.0101 1.0000 0.0441
-8.500 -0.8627 0.01528 0.00876 -0.0091 1.0000 0.0452
-8.250 -0.8394 0.01484 0.00828 -0.0080 1.0000 0.0463
-8.000 -0.8174 0.01425 0.00769 -0.0067 1.0000 0.0477
-7.750 -0.7945 0.01377 0.00723 -0.0056 1.0000 0.0494
-7.500 -0.7711 0.01337 0.00682 -0.0045 1.0000 0.0514
-7.250 -0.7482 0.01291 0.00639 -0.0033 1.0000 0.0542
-7.000 -0.7247 0.01254 0.00603 -0.0022 1.0000 0.0582
-6.750 -0.7012 0.01216 0.00571 -0.0011 1.0000 0.0649
-6.500 -0.6771 0.01187 0.00550 -0.0001 1.0000 0.0742
-6.250 -0.6523 0.01171 0.00537 0.0008 1.0000 0.0827
-6.000 -0.6274 0.01158 0.00528 0.0017 1.0000 0.0890
-5.750 -0.6030 0.01140 0.00512 0.0027 1.0000 0.0937
-5.500 -0.5785 0.01126 0.00501 0.0037 1.0000 0.0981
-5.250 -0.5537 0.01118 0.00491 0.0047 1.0000 0.1015
-5.000 -0.5203 0.01087 0.00466 0.0037 0.9960 0.1060
-4.750 -0.4748 0.01070 0.00451 0.0003 0.9788 0.1109
-4.500 -0.4234 0.01047 0.00427 -0.0042 0.9460 0.1153
-4.250 -0.3747 0.01028 0.00393 -0.0080 0.8494 0.1205
-4.000 -0.3546 0.01062 0.00375 -0.0058 0.7009 0.1240
-3.750 -0.3305 0.01083 0.00363 -0.0046 0.6302 0.1271
-3.500 -0.3057 0.01071 0.00341 -0.0037 0.5916 0.1323
-3.250 -0.2796 0.01069 0.00329 -0.0031 0.5617 0.1370
-3.000 -0.2527 0.01068 0.00317 -0.0025 0.5367 0.1412
-2.750 -0.2266 0.01052 0.00299 -0.0019 0.5153 0.1478
-2.500 -0.1997 0.01047 0.00288 -0.0014 0.4966 0.1544
-2.250 -0.1731 0.01035 0.00274 -0.0008 0.4798 0.1623
-2.000 -0.1462 0.01028 0.00263 -0.0003 0.4644 0.1719
-1.750 -0.1196 0.01014 0.00251 0.0002 0.4497 0.1862
-1.500 -0.0929 0.00999 0.00239 0.0008 0.4362 0.2063
-1.250 -0.0669 0.00976 0.00229 0.0013 0.4237 0.2431
-1.000 -0.0421 0.00942 0.00221 0.0020 0.4113 0.3239
-0.750 -0.0169 0.00909 0.00215 0.0027 0.3993 0.4032
-0.500 0.0076 0.00879 0.00211 0.0036 0.3877 0.4879
-0.250 0.0313 0.00849 0.00210 0.0047 0.3761 0.5798
0.000 0.0551 0.00824 0.00213 0.0059 0.3654 0.6645
0.250 0.0792 0.00811 0.00216 0.0071 0.3544 0.7295
0.500 0.1040 0.00798 0.00221 0.0082 0.3436 0.7842
0.750 0.1294 0.00793 0.00228 0.0093 0.3332 0.8338
1.000 0.1567 0.00795 0.00236 0.0101 0.3221 0.8794
1.250 0.1886 0.00803 0.00247 0.0099 0.3106 0.9173
1.500 0.2264 0.00820 0.00258 0.0083 0.2991 0.9424
1.750 0.2640 0.00835 0.00266 0.0068 0.2888 0.9570
2.000 0.3017 0.00852 0.00277 0.0051 0.2802 0.9690
2.250 0.3467 0.00871 0.00289 0.0020 0.2718 0.9775
2.500 0.3925 0.00891 0.00301 -0.0014 0.2644 0.9854
2.750 0.4351 0.00904 0.00310 -0.0042 0.2580 0.9916
3.000 0.4770 0.00920 0.00318 -0.0069 0.2518 0.9962
3.250 0.5187 0.00929 0.00325 -0.0095 0.2468 1.0000
3.500 0.5418 0.00937 0.00332 -0.0084 0.2421 1.0000
3.750 0.5647 0.00951 0.00341 -0.0073 0.2374 1.0000
4.000 0.5877 0.00968 0.00354 -0.0062 0.2330 1.0000
4.250 0.6116 0.00977 0.00365 -0.0052 0.2293 1.0000
4.500 0.6354 0.00989 0.00376 -0.0042 0.2249 1.0000
4.750 0.6587 0.01009 0.00390 -0.0031 0.2198 1.0000
5.000 0.6826 0.01024 0.00406 -0.0021 0.2153 1.0000
5.250 0.7070 0.01035 0.00419 -0.0012 0.2104 1.0000
5.500 0.7308 0.01054 0.00433 -0.0002 0.2051 1.0000
5.750 0.7549 0.01073 0.00452 0.0007 0.1998 1.0000
6.000 0.7796 0.01084 0.00466 0.0016 0.1937 1.0000
6.250 0.8033 0.01109 0.00484 0.0025 0.1865 1.0000
6.500 0.8285 0.01119 0.00499 0.0033 0.1794 1.0000
6.750 0.8523 0.01145 0.00519 0.0042 0.1715 1.0000
7.000 0.8771 0.01162 0.00537 0.0050 0.1633 1.0000
7.250 0.9011 0.01190 0.00560 0.0059 0.1552 1.0000
7.500 0.9249 0.01219 0.00584 0.0067 0.1472 1.0000
7.750 0.9487 0.01248 0.00613 0.0076 0.1407 1.0000
8.000 0.9719 0.01285 0.00644 0.0085 0.1345 1.0000
8.250 0.9954 0.01319 0.00680 0.0094 0.1302 1.0000
8.500 1.0190 0.01352 0.00714 0.0102 0.1261 1.0000
8.750 1.0414 0.01397 0.00756 0.0112 0.1220 1.0000
9.000 1.0645 0.01435 0.00797 0.0121 0.1188 1.0000
9.250 1.0882 0.01468 0.00834 0.0129 0.1158 1.0000
9.500 1.1109 0.01510 0.00877 0.0137 0.1126 1.0000
9.750 1.1316 0.01571 0.00935 0.0148 0.1091 1.0000
10.000 1.1555 0.01600 0.00972 0.0155 0.1068 1.0000
10.250 1.1787 0.01636 0.01013 0.0163 0.1039 1.0000
10.500 1.2004 0.01684 0.01061 0.0172 0.1007 1.0000
10.750 1.2208 0.01743 0.01122 0.0183 0.0977 1.0000
11.000 1.2441 0.01775 0.01162 0.0190 0.0951 1.0000
11.250 1.2660 0.01817 0.01208 0.0198 0.0920 1.0000
11.500 1.2844 0.01886 0.01275 0.0210 0.0887 1.0000
11.750 1.3070 0.01920 0.01319 0.0217 0.0858 1.0000
12.000 1.3278 0.01967 0.01369 0.0226 0.0822 1.0000
12.250 1.3455 0.02034 0.01437 0.0238 0.0786 1.0000
12.500 1.3658 0.02080 0.01490 0.0247 0.0746 1.0000
12.750 1.3806 0.02162 0.01570 0.0262 0.0708 1.0000
13.000 1.3978 0.02224 0.01639 0.0274 0.0670 1.0000
13.250 1.4078 0.02326 0.01740 0.0292 0.0638 1.0000
13.500 1.4189 0.02405 0.01828 0.0312 0.0610 1.0000
13.750 1.4225 0.02508 0.01935 0.0338 0.0588 1.0000
14.000 1.4190 0.02663 0.02093 0.0365 0.0570 1.0000
14.250 1.4210 0.02813 0.02254 0.0379 0.0555 1.0000
14.500 1.4198 0.03020 0.02471 0.0385 0.0540 1.0000
14.750 1.4143 0.03330 0.02792 0.0376 0.0529 1.0000
15.000 1.4053 0.03770 0.03243 0.0350 0.0520 1.0000
15.250 1.3918 0.04288 0.03771 0.0319 0.0513 1.0000
15.500 1.3748 0.04834 0.04327 0.0291 0.0506 1.0000
15.750 1.3626 0.05312 0.04818 0.0268 0.0500 1.0000
16.000 1.3484 0.05810 0.05327 0.0245 0.0495 1.0000
16.250 1.3333 0.06320 0.05847 0.0222 0.0489 1.0000
16.500 1.3185 0.06828 0.06364 0.0198 0.0483 1.0000
16.750 1.3044 0.07332 0.06877 0.0175 0.0478 1.0000
17.000 1.2920 0.07831 0.07382 0.0151 0.0472 1.0000
17.250 1.2814 0.08319 0.07876 0.0128 0.0467 1.0000
17.500 1.2731 0.08776 0.08335 0.0107 0.0460 1.0000
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Polar data table (+)
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