GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 527 AIRFOIL (goe527-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.85 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe527-il-1000000.txt Download as CSV file: xf-goe527-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7118 0.06691 0.06435 -0.0895 1.0000 0.0257
-15.500 -0.7694 0.05521 0.05244 -0.0978 1.0000 0.0257
-15.250 -0.8028 0.04761 0.04469 -0.1030 1.0000 0.0257
-15.000 -0.8259 0.04179 0.03874 -0.1071 0.9998 0.0256
-14.750 -0.8348 0.03328 0.02993 -0.1202 0.9949 0.0260
-14.500 -0.8258 0.03012 0.02664 -0.1244 0.9872 0.0262
-14.250 -0.8069 0.02814 0.02460 -0.1273 0.9813 0.0265
-13.750 -0.7648 0.02549 0.02180 -0.1302 0.9617 0.0270
-13.500 -0.7295 0.02419 0.02040 -0.1338 0.9549 0.0273
-13.250 -0.6947 0.02295 0.01904 -0.1370 0.9432 0.0277
-13.000 -0.6613 0.02192 0.01786 -0.1397 0.9275 0.0281
-12.750 -0.6369 0.02124 0.01703 -0.1400 0.9084 0.0285
-12.500 -0.6204 0.02060 0.01622 -0.1387 0.8895 0.0287
-12.250 -0.6053 0.02003 0.01550 -0.1369 0.8726 0.0290
-12.000 -0.5893 0.01952 0.01486 -0.1351 0.8571 0.0291
-11.750 -0.5724 0.01905 0.01425 -0.1334 0.8430 0.0293
-11.500 -0.5601 0.01807 0.01310 -0.1313 0.8291 0.0296
-11.250 -0.5447 0.01726 0.01220 -0.1295 0.8169 0.0300
-11.000 -0.5264 0.01671 0.01157 -0.1280 0.8060 0.0304
-10.750 -0.5063 0.01629 0.01108 -0.1267 0.7949 0.0307
-10.500 -0.4852 0.01589 0.01061 -0.1255 0.7849 0.0310
-10.000 -0.4414 0.01519 0.00975 -0.1234 0.7651 0.0319
-9.500 -0.3963 0.01447 0.00886 -0.1213 0.7476 0.0326
-9.250 -0.3735 0.01413 0.00843 -0.1204 0.7390 0.0329
-9.000 -0.3496 0.01382 0.00805 -0.1195 0.7314 0.0332
-8.750 -0.3259 0.01351 0.00766 -0.1187 0.7230 0.0335
-8.500 -0.3052 0.01290 0.00698 -0.1174 0.7153 0.0342
-8.250 -0.2816 0.01254 0.00658 -0.1166 0.7073 0.0347
-8.000 -0.2575 0.01230 0.00628 -0.1157 0.6993 0.0353
-7.750 -0.2322 0.01204 0.00600 -0.1151 0.6923 0.0359
-7.500 -0.2074 0.01182 0.00571 -0.1144 0.6846 0.0365
-7.250 -0.1821 0.01159 0.00543 -0.1137 0.6774 0.0371
-7.000 -0.1567 0.01139 0.00516 -0.1131 0.6694 0.0376
-6.750 -0.1322 0.01113 0.00484 -0.1123 0.6616 0.0383
-6.500 -0.1074 0.01082 0.00451 -0.1116 0.6539 0.0393
-6.250 -0.0823 0.01065 0.00428 -0.1109 0.6460 0.0401
-6.000 -0.0561 0.01048 0.00408 -0.1104 0.6388 0.0412
-5.750 -0.0302 0.01034 0.00389 -0.1098 0.6307 0.0422
-5.500 -0.0047 0.01015 0.00366 -0.1092 0.6231 0.0437
-5.250 0.0212 0.00999 0.00348 -0.1087 0.6153 0.0456
-5.000 0.0470 0.00989 0.00333 -0.1081 0.6079 0.0475
-4.750 0.0733 0.00972 0.00316 -0.1076 0.6011 0.0504
-4.500 0.0993 0.00962 0.00303 -0.1071 0.5937 0.0541
-4.250 0.1256 0.00951 0.00293 -0.1066 0.5871 0.0596
-4.000 0.1522 0.00942 0.00285 -0.1062 0.5805 0.0660
-3.750 0.1783 0.00939 0.00280 -0.1057 0.5740 0.0716
-3.500 0.2057 0.00936 0.00276 -0.1054 0.5687 0.0761
-3.250 0.2325 0.00930 0.00272 -0.1050 0.5630 0.0811
-3.000 0.2591 0.00932 0.00269 -0.1046 0.5570 0.0844
-2.750 0.2858 0.00925 0.00263 -0.1042 0.5524 0.0884
-2.500 0.3130 0.00921 0.00259 -0.1040 0.5478 0.0920
-2.250 0.3399 0.00921 0.00256 -0.1036 0.5429 0.0947
-2.000 0.3656 0.00920 0.00251 -0.1031 0.5376 0.0986
-1.750 0.3929 0.00913 0.00246 -0.1028 0.5340 0.1028
-1.500 0.4200 0.00910 0.00243 -0.1025 0.5296 0.1062
-1.250 0.4463 0.00909 0.00239 -0.1021 0.5246 0.1101
-1.000 0.4718 0.00908 0.00236 -0.1015 0.5190 0.1165
-0.750 0.4991 0.00902 0.00233 -0.1013 0.5153 0.1233
-0.500 0.5254 0.00895 0.00230 -0.1009 0.5110 0.1358
-0.250 0.5500 0.00880 0.00229 -0.1002 0.5063 0.1857
0.000 0.5738 0.00863 0.00232 -0.0994 0.5010 0.2605
0.250 0.5989 0.00841 0.00233 -0.0989 0.4968 0.3359
0.500 0.6232 0.00824 0.00236 -0.0982 0.4923 0.4142
0.750 0.6470 0.00812 0.00242 -0.0974 0.4882 0.4866
1.000 0.6701 0.00804 0.00249 -0.0964 0.4840 0.5564
1.250 0.6936 0.00784 0.00255 -0.0955 0.4813 0.6385
1.500 0.7133 0.00757 0.00262 -0.0937 0.4781 0.7585
1.750 0.7383 0.00730 0.00282 -0.0927 0.4744 0.9356
2.000 0.7906 0.00748 0.00296 -0.0979 0.4696 0.9692
2.250 0.8351 0.00763 0.00307 -0.1014 0.4653 0.9808
2.500 0.8811 0.00774 0.00315 -0.1052 0.4604 0.9871
2.750 0.9238 0.00789 0.00325 -0.1084 0.4546 0.9941
3.000 0.9663 0.00805 0.00334 -0.1117 0.4488 0.9982
3.250 1.0040 0.00812 0.00341 -0.1138 0.4446 1.0000
3.500 1.0245 0.00820 0.00347 -0.1123 0.4403 1.0000
3.750 1.0435 0.00832 0.00355 -0.1106 0.4355 1.0000
4.000 1.0630 0.00842 0.00363 -0.1089 0.4311 1.0000
4.250 1.0838 0.00850 0.00370 -0.1075 0.4261 1.0000
4.500 1.1023 0.00863 0.00379 -0.1056 0.4194 1.0000
4.750 1.1213 0.00876 0.00390 -0.1039 0.4137 1.0000
5.000 1.1416 0.00886 0.00399 -0.1024 0.4078 1.0000
5.250 1.1598 0.00902 0.00411 -0.1005 0.4014 1.0000
5.500 1.1796 0.00916 0.00424 -0.0990 0.3956 1.0000
5.750 1.1977 0.00931 0.00436 -0.0971 0.3888 1.0000
6.000 1.2118 0.00950 0.00451 -0.0944 0.3818 1.0000
6.250 1.2294 0.00964 0.00465 -0.0924 0.3749 1.0000
6.500 1.2434 0.00989 0.00484 -0.0898 0.3664 1.0000
6.750 1.2617 0.01007 0.00502 -0.0881 0.3586 1.0000
7.000 1.2765 0.01036 0.00525 -0.0858 0.3490 1.0000
7.250 1.2932 0.01062 0.00549 -0.0839 0.3390 1.0000
7.500 1.3085 0.01095 0.00577 -0.0818 0.3282 1.0000
7.750 1.3223 0.01135 0.00611 -0.0795 0.3172 1.0000
8.000 1.3385 0.01169 0.00642 -0.0777 0.3074 1.0000
8.250 1.3531 0.01210 0.00680 -0.0756 0.2980 1.0000
8.500 1.3669 0.01257 0.00722 -0.0736 0.2882 1.0000
8.750 1.3827 0.01299 0.00763 -0.0719 0.2803 1.0000
9.000 1.3961 0.01353 0.00813 -0.0699 0.2722 1.0000
9.250 1.4116 0.01401 0.00860 -0.0684 0.2651 1.0000
9.500 1.4254 0.01459 0.00916 -0.0666 0.2584 1.0000
9.750 1.4399 0.01517 0.00973 -0.0651 0.2526 1.0000
10.000 1.4559 0.01570 0.01027 -0.0638 0.2480 1.0000
10.250 1.4694 0.01639 0.01095 -0.0623 0.2432 1.0000
10.500 1.4830 0.01711 0.01167 -0.0609 0.2386 1.0000
10.750 1.4996 0.01768 0.01228 -0.0599 0.2357 1.0000
11.000 1.5145 0.01838 0.01299 -0.0588 0.2323 1.0000
11.250 1.5276 0.01921 0.01383 -0.0575 0.2286 1.0000
11.500 1.5385 0.02020 0.01483 -0.0562 0.2247 1.0000
11.750 1.5539 0.02094 0.01561 -0.0553 0.2221 1.0000
12.000 1.5686 0.02173 0.01644 -0.0544 0.2192 1.0000
12.250 1.5809 0.02272 0.01745 -0.0534 0.2158 1.0000
12.500 1.5883 0.02406 0.01878 -0.0521 0.2106 1.0000
12.750 1.6008 0.02507 0.01983 -0.0512 0.2073 1.0000
13.000 1.6139 0.02607 0.02087 -0.0504 0.2039 1.0000
13.250 1.6226 0.02740 0.02222 -0.0494 0.1993 1.0000
13.500 1.6273 0.02909 0.02391 -0.0482 0.1943 1.0000
13.750 1.6403 0.03015 0.02502 -0.0476 0.1906 1.0000
14.000 1.6491 0.03157 0.02646 -0.0468 0.1864 1.0000
14.250 1.6518 0.03351 0.02840 -0.0458 0.1806 1.0000
14.500 1.6609 0.03497 0.02991 -0.0451 0.1760 1.0000
14.750 1.6638 0.03699 0.03193 -0.0442 0.1692 1.0000
15.000 1.6663 0.03905 0.03400 -0.0434 0.1624 1.0000
15.250 1.6646 0.04156 0.03650 -0.0425 0.1543 1.0000
15.500 1.6653 0.04390 0.03886 -0.0417 0.1481 1.0000
15.750 1.6592 0.04691 0.04185 -0.0409 0.1405 1.0000
16.000 1.6575 0.04956 0.04453 -0.0402 0.1355 1.0000
16.250 1.6526 0.05257 0.04755 -0.0396 0.1307 1.0000
16.500 1.6510 0.05528 0.05029 -0.0392 0.1269 1.0000
16.750 1.6492 0.05804 0.05310 -0.0388 0.1239 1.0000
17.000 1.6458 0.06103 0.05612 -0.0384 0.1212 1.0000
17.250 1.6427 0.06399 0.05911 -0.0381 0.1186 1.0000
17.500 1.6417 0.06678 0.06196 -0.0380 0.1166 1.0000
17.750 1.6436 0.06923 0.06447 -0.0378 0.1151 1.0000
18.000 1.6425 0.07204 0.06734 -0.0378 0.1132 1.0000
18.250 1.6408 0.07494 0.07029 -0.0377 0.1113 1.0000
18.500 1.6348 0.07837 0.07375 -0.0378 0.1086 1.0000
18.750 1.6269 0.08203 0.07746 -0.0378 0.1061 1.0000
19.000 1.6314 0.08423 0.07973 -0.0379 0.1049 1.0000
19.250 1.6321 0.08692 0.08248 -0.0381 0.1029 1.0000
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