GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.16 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe497-il-1000000-n5.txt Download as CSV file: xf-goe497-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7577 0.08020 0.07764 -0.0773 1.0000 0.0170
-15.500 -0.7968 0.07161 0.06896 -0.0821 1.0000 0.0169
-15.250 -0.8441 0.06292 0.06016 -0.0867 1.0000 0.0169
-15.000 -0.8899 0.05149 0.04855 -0.0978 0.9977 0.0166
-14.750 -0.9342 0.03828 0.03511 -0.1140 0.9843 0.0164
-14.500 -0.9313 0.02540 0.02185 -0.1374 0.9735 0.0167
-14.250 -0.9024 0.02311 0.01943 -0.1425 0.9703 0.0175
-14.000 -0.8758 0.02165 0.01785 -0.1452 0.9645 0.0182
-13.750 -0.8449 0.02049 0.01658 -0.1479 0.9599 0.0188
-13.500 -0.8180 0.01939 0.01540 -0.1496 0.9523 0.0196
-13.250 -0.7892 0.01853 0.01446 -0.1512 0.9442 0.0205
-13.000 -0.7645 0.01784 0.01369 -0.1517 0.9345 0.0212
-12.750 -0.7388 0.01724 0.01299 -0.1521 0.9267 0.0219
-12.500 -0.7145 0.01671 0.01237 -0.1521 0.9189 0.0224
-12.000 -0.6658 0.01556 0.01106 -0.1521 0.9046 0.0237
-11.750 -0.6408 0.01509 0.01053 -0.1521 0.8974 0.0244
-11.500 -0.6154 0.01468 0.01004 -0.1520 0.8910 0.0252
-11.250 -0.5898 0.01430 0.00959 -0.1519 0.8845 0.0259
-11.000 -0.5638 0.01395 0.00915 -0.1518 0.8787 0.0264
-10.750 -0.5376 0.01361 0.00874 -0.1517 0.8730 0.0268
-10.500 -0.5122 0.01313 0.00819 -0.1516 0.8668 0.0276
-10.250 -0.4860 0.01277 0.00778 -0.1515 0.8612 0.0285
-10.000 -0.4595 0.01244 0.00741 -0.1515 0.8553 0.0293
-9.750 -0.4328 0.01216 0.00706 -0.1513 0.8494 0.0300
-9.500 -0.4059 0.01189 0.00672 -0.1513 0.8443 0.0307
-9.250 -0.3787 0.01162 0.00639 -0.1512 0.8391 0.0313
-9.000 -0.3517 0.01134 0.00604 -0.1511 0.8337 0.0320
-8.750 -0.3248 0.01102 0.00568 -0.1510 0.8281 0.0331
-8.500 -0.2975 0.01075 0.00538 -0.1510 0.8221 0.0340
-8.250 -0.2704 0.01053 0.00509 -0.1508 0.8149 0.0348
-8.000 -0.2429 0.01031 0.00482 -0.1508 0.8081 0.0356
-7.750 -0.2155 0.01013 0.00457 -0.1506 0.8007 0.0365
-7.500 -0.1879 0.00995 0.00432 -0.1505 0.7947 0.0372
-7.250 -0.1602 0.00969 0.00404 -0.1505 0.7891 0.0386
-7.000 -0.1325 0.00950 0.00381 -0.1504 0.7828 0.0399
-6.750 -0.1047 0.00933 0.00360 -0.1503 0.7766 0.0413
-6.500 -0.0769 0.00918 0.00340 -0.1502 0.7689 0.0426
-6.250 -0.0492 0.00905 0.00321 -0.1501 0.7622 0.0439
-6.000 -0.0211 0.00886 0.00301 -0.1501 0.7556 0.0464
-5.750 0.0066 0.00872 0.00283 -0.1500 0.7485 0.0488
-5.500 0.0347 0.00861 0.00268 -0.1499 0.7416 0.0507
-5.250 0.0625 0.00847 0.00251 -0.1498 0.7333 0.0541
-5.000 0.0904 0.00835 0.00237 -0.1497 0.7251 0.0576
-4.750 0.1181 0.00825 0.00224 -0.1496 0.7163 0.0617
-4.500 0.1460 0.00814 0.00211 -0.1495 0.7083 0.0677
-4.250 0.1736 0.00803 0.00201 -0.1494 0.6996 0.0762
-4.000 0.2015 0.00793 0.00191 -0.1493 0.6907 0.0854
-3.750 0.2291 0.00790 0.00183 -0.1491 0.6818 0.0918
-3.500 0.2571 0.00782 0.00176 -0.1490 0.6735 0.0985
-3.250 0.2847 0.00780 0.00169 -0.1488 0.6650 0.1038
-3.000 0.3127 0.00775 0.00163 -0.1487 0.6565 0.1093
-2.750 0.3402 0.00772 0.00158 -0.1485 0.6478 0.1169
-2.500 0.3681 0.00768 0.00153 -0.1484 0.6393 0.1244
-2.250 0.3957 0.00766 0.00150 -0.1482 0.6316 0.1335
-2.000 0.4237 0.00760 0.00146 -0.1482 0.6245 0.1467
-1.500 0.4789 0.00753 0.00143 -0.1479 0.6075 0.1797
-1.250 0.5061 0.00753 0.00143 -0.1476 0.5972 0.1975
-1.000 0.5340 0.00751 0.00143 -0.1475 0.5890 0.2132
-0.750 0.5614 0.00752 0.00145 -0.1473 0.5812 0.2256
-0.500 0.5892 0.00753 0.00146 -0.1472 0.5723 0.2360
-0.250 0.6165 0.00756 0.00149 -0.1470 0.5627 0.2482
0.000 0.6435 0.00761 0.00152 -0.1467 0.5503 0.2594
0.250 0.6700 0.00770 0.00156 -0.1463 0.5335 0.2685
0.500 0.6957 0.00783 0.00163 -0.1458 0.5095 0.2789
0.750 0.7208 0.00801 0.00172 -0.1452 0.4853 0.2881
1.000 0.7464 0.00817 0.00181 -0.1447 0.4665 0.2982
1.250 0.7722 0.00831 0.00191 -0.1442 0.4527 0.3090
1.500 0.7983 0.00842 0.00201 -0.1438 0.4405 0.3238
1.750 0.8245 0.00852 0.00211 -0.1434 0.4307 0.3416
2.000 0.8507 0.00862 0.00222 -0.1431 0.4226 0.3561
2.250 0.8773 0.00870 0.00232 -0.1427 0.4165 0.3719
2.500 0.9037 0.00879 0.00243 -0.1424 0.4093 0.3890
2.750 0.9296 0.00891 0.00255 -0.1420 0.4029 0.4038
3.000 0.9565 0.00897 0.00265 -0.1417 0.3984 0.4171
3.250 0.9830 0.00905 0.00276 -0.1414 0.3935 0.4306
3.500 1.0090 0.00915 0.00289 -0.1410 0.3885 0.4460
3.750 1.0351 0.00924 0.00301 -0.1406 0.3840 0.4606
4.000 1.0611 0.00935 0.00314 -0.1402 0.3765 0.4746
4.250 1.0857 0.00951 0.00330 -0.1395 0.3633 0.4910
4.500 1.1094 0.00973 0.00347 -0.1387 0.3441 0.5087
4.750 1.1318 0.01000 0.00368 -0.1378 0.3210 0.5281
5.000 1.1531 0.01032 0.00393 -0.1366 0.2936 0.5550
5.250 1.1733 0.01066 0.00423 -0.1352 0.2678 0.5942
5.500 1.1928 0.01075 0.00459 -0.1338 0.2500 0.7460
6.000 1.2348 0.01104 0.00515 -0.1312 0.2236 1.0000
6.250 1.2571 0.01130 0.00539 -0.1302 0.2170 1.0000
6.500 1.2789 0.01157 0.00563 -0.1291 0.2112 1.0000
6.750 1.3004 0.01178 0.00585 -0.1279 0.2064 1.0000
7.000 1.3197 0.01208 0.00611 -0.1263 0.1995 1.0000
7.250 1.3395 0.01235 0.00638 -0.1248 0.1937 1.0000
7.500 1.3584 0.01266 0.00666 -0.1232 0.1847 1.0000
7.750 1.3765 0.01301 0.00697 -0.1215 0.1747 1.0000
8.000 1.3895 0.01361 0.00742 -0.1190 0.1506 1.0000
8.250 1.3963 0.01451 0.00812 -0.1156 0.1180 1.0000
8.500 1.4080 0.01519 0.00872 -0.1130 0.1028 1.0000
8.750 1.4220 0.01578 0.00926 -0.1109 0.0925 1.0000
9.000 1.4364 0.01635 0.00980 -0.1089 0.0854 1.0000
9.250 1.4515 0.01691 0.01034 -0.1070 0.0793 1.0000
9.500 1.4661 0.01750 0.01092 -0.1051 0.0743 1.0000
9.750 1.4818 0.01804 0.01147 -0.1034 0.0706 1.0000
10.000 1.4960 0.01868 0.01210 -0.1016 0.0667 1.0000
10.250 1.5104 0.01933 0.01275 -0.0999 0.0630 1.0000
10.500 1.5246 0.02000 0.01343 -0.0982 0.0595 1.0000
10.750 1.5370 0.02079 0.01422 -0.0963 0.0558 1.0000
11.000 1.5513 0.02149 0.01494 -0.0947 0.0537 1.0000
11.250 1.5650 0.02224 0.01572 -0.0931 0.0515 1.0000
11.500 1.5772 0.02312 0.01660 -0.0915 0.0488 1.0000
11.750 1.5887 0.02406 0.01756 -0.0898 0.0457 1.0000
12.000 1.6006 0.02500 0.01852 -0.0882 0.0428 1.0000
12.250 1.6096 0.02617 0.01968 -0.0864 0.0388 1.0000
12.500 1.6190 0.02735 0.02087 -0.0848 0.0345 1.0000
12.750 1.6249 0.02883 0.02233 -0.0829 0.0285 1.0000
13.000 1.6265 0.03070 0.02417 -0.0809 0.0208 1.0000
13.250 1.6300 0.03249 0.02597 -0.0791 0.0172 1.0000
13.500 1.6351 0.03421 0.02773 -0.0776 0.0153 1.0000
13.750 1.6412 0.03592 0.02948 -0.0763 0.0142 1.0000
14.000 1.6463 0.03776 0.03137 -0.0750 0.0133 1.0000
14.250 1.6528 0.03953 0.03319 -0.0740 0.0125 1.0000
14.500 1.6580 0.04148 0.03521 -0.0730 0.0119 1.0000
14.750 1.6619 0.04363 0.03742 -0.0720 0.0113 1.0000
15.000 1.6654 0.04590 0.03974 -0.0712 0.0108 1.0000
15.250 1.6698 0.04812 0.04203 -0.0705 0.0104 1.0000
15.500 1.6741 0.05041 0.04440 -0.0700 0.0102 1.0000
15.750 1.6773 0.05290 0.04696 -0.0695 0.0098 1.0000
16.000 1.6798 0.05554 0.04967 -0.0692 0.0095 1.0000
16.250 1.6811 0.05837 0.05257 -0.0689 0.0093 1.0000
16.500 1.6813 0.06141 0.05569 -0.0688 0.0090 1.0000
16.750 1.6808 0.06464 0.05900 -0.0689 0.0087 1.0000
17.000 1.6787 0.06817 0.06260 -0.0691 0.0084 1.0000
17.250 1.6782 0.07153 0.06605 -0.0694 0.0082 1.0000
17.500 1.6775 0.07501 0.06962 -0.0699 0.0081 1.0000
17.750 1.6759 0.07870 0.07340 -0.0705 0.0080 1.0000
18.000 1.6736 0.08259 0.07737 -0.0713 0.0077 1.0000
18.250 1.6705 0.08666 0.08153 -0.0722 0.0076 1.0000
18.500 1.6666 0.09092 0.08588 -0.0734 0.0074 1.0000
18.750 1.6620 0.09538 0.09044 -0.0747 0.0072 1.0000
19.000 1.6567 0.10000 0.09516 -0.0762 0.0071 1.0000
19.250 1.6511 0.10474 0.09999 -0.0778 0.0070 1.0000
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