GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 459 AIRFOIL (goe459-il) Reynolds number: 500,000 Max Cl/Cd: 60.18 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe459-il-500000-n5.txt Download as CSV file: xf-goe459-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 459 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0255 0.10451 0.10074 -0.0225 1.0000 0.0088
-17.750 -1.0552 0.09535 0.09145 -0.0272 1.0000 0.0087
-17.500 -1.0810 0.08707 0.08301 -0.0313 1.0000 0.0088
-17.250 -1.1034 0.07947 0.07527 -0.0352 1.0000 0.0088
-17.000 -1.1246 0.07230 0.06795 -0.0389 1.0000 0.0088
-16.750 -1.1422 0.06599 0.06149 -0.0420 1.0000 0.0089
-16.500 -1.1598 0.06001 0.05536 -0.0448 1.0000 0.0088
-16.250 -1.1701 0.05535 0.05056 -0.0468 1.0000 0.0088
-16.000 -1.1797 0.05099 0.04607 -0.0484 1.0000 0.0091
-15.750 -1.1871 0.04715 0.04210 -0.0496 1.0000 0.0091
-15.500 -1.1940 0.04358 0.03840 -0.0504 1.0000 0.0092
-15.250 -1.2022 0.04014 0.03484 -0.0507 1.0000 0.0095
-15.000 -1.2042 0.03753 0.03213 -0.0505 1.0000 0.0096
-14.750 -1.2045 0.03526 0.02977 -0.0500 1.0000 0.0100
-14.500 -1.2043 0.03318 0.02757 -0.0491 1.0000 0.0101
-14.250 -1.2010 0.03150 0.02580 -0.0480 1.0000 0.0105
-14.000 -1.1980 0.02989 0.02409 -0.0465 1.0000 0.0108
-13.750 -1.1926 0.02857 0.02267 -0.0450 1.0000 0.0111
-13.500 -1.1871 0.02733 0.02133 -0.0432 1.0000 0.0114
-13.250 -1.1801 0.02627 0.02016 -0.0412 1.0000 0.0118
-13.000 -1.1750 0.02513 0.01895 -0.0389 1.0000 0.0122
-12.750 -1.1697 0.02409 0.01783 -0.0364 1.0000 0.0128
-12.500 -1.1630 0.02319 0.01686 -0.0337 1.0000 0.0133
-12.250 -1.1558 0.02239 0.01599 -0.0310 1.0000 0.0140
-12.000 -1.1477 0.02170 0.01523 -0.0281 1.0000 0.0146
-11.750 -1.1409 0.02100 0.01447 -0.0249 1.0000 0.0160
-11.500 -1.1352 0.02033 0.01377 -0.0214 1.0000 0.0175
-11.000 -1.1237 0.01916 0.01266 -0.0140 1.0000 0.0259
-10.750 -1.1108 0.01876 0.01228 -0.0114 1.0000 0.0307
-10.500 -1.0955 0.01844 0.01195 -0.0092 1.0000 0.0343
-10.250 -1.0802 0.01813 0.01158 -0.0070 1.0000 0.0363
-10.000 -1.0653 0.01778 0.01124 -0.0048 1.0000 0.0382
-9.750 -1.0489 0.01751 0.01095 -0.0028 1.0000 0.0402
-9.500 -1.0324 0.01726 0.01065 -0.0007 1.0000 0.0418
-9.250 -1.0156 0.01701 0.01035 0.0013 1.0000 0.0430
-9.000 -0.9986 0.01679 0.01008 0.0033 1.0000 0.0438
-8.750 -0.9852 0.01637 0.00963 0.0059 1.0000 0.0452
-8.500 -0.9582 0.01594 0.00919 0.0056 0.9986 0.0472
-8.250 -0.9272 0.01560 0.00883 0.0046 0.9965 0.0492
-8.000 -0.8961 0.01527 0.00846 0.0035 0.9943 0.0506
-7.750 -0.8668 0.01492 0.00807 0.0029 0.9918 0.0518
-7.500 -0.8366 0.01463 0.00774 0.0022 0.9890 0.0531
-7.250 -0.8051 0.01438 0.00745 0.0012 0.9864 0.0541
-7.000 -0.7739 0.01391 0.00695 0.0001 0.9841 0.0559
-6.750 -0.7468 0.01350 0.00651 0.0000 0.9790 0.0573
-6.500 -0.7149 0.01311 0.00610 -0.0010 0.9749 0.0587
-6.250 -0.6849 0.01276 0.00574 -0.0016 0.9695 0.0603
-6.000 -0.6555 0.01243 0.00539 -0.0021 0.9635 0.0620
-5.750 -0.6241 0.01213 0.00507 -0.0029 0.9595 0.0638
-5.500 -0.5987 0.01187 0.00479 -0.0024 0.9521 0.0659
-5.250 -0.5673 0.01154 0.00448 -0.0033 0.9477 0.0709
-5.000 -0.5385 0.01122 0.00420 -0.0036 0.9412 0.0782
-4.750 -0.5076 0.01072 0.00386 -0.0045 0.9354 0.1084
-4.500 -0.4717 0.01030 0.00359 -0.0065 0.9313 0.1396
-4.250 -0.4389 0.01001 0.00336 -0.0077 0.9238 0.1581
-4.000 -0.4017 0.00969 0.00311 -0.0099 0.9174 0.1792
-3.750 -0.3685 0.00933 0.00289 -0.0113 0.9080 0.2097
-3.500 -0.3344 0.00901 0.00268 -0.0128 0.8989 0.2429
-3.250 -0.3044 0.00877 0.00252 -0.0133 0.8875 0.2707
-3.000 -0.2763 0.00853 0.00236 -0.0134 0.8749 0.3010
-2.750 -0.2499 0.00830 0.00221 -0.0132 0.8603 0.3307
-2.500 -0.2250 0.00808 0.00208 -0.0125 0.8434 0.3635
-2.250 -0.2019 0.00787 0.00196 -0.0115 0.8251 0.4042
-2.000 -0.1790 0.00771 0.00188 -0.0104 0.8070 0.4439
-1.750 -0.1558 0.00761 0.00181 -0.0093 0.7888 0.4742
-1.500 -0.1327 0.00752 0.00174 -0.0082 0.7708 0.4995
-1.250 -0.1106 0.00742 0.00169 -0.0068 0.7529 0.5288
-1.000 -0.0887 0.00734 0.00165 -0.0054 0.7342 0.5573
-0.500 -0.0449 0.00726 0.00160 -0.0026 0.6938 0.6072
0.000 0.0000 0.00722 0.00159 0.0000 0.6539 0.6536
0.250 0.0223 0.00724 0.00159 0.0013 0.6313 0.6741
0.500 0.0448 0.00726 0.00160 0.0026 0.6068 0.6939
1.000 0.0889 0.00733 0.00165 0.0054 0.5590 0.7343
1.250 0.1106 0.00742 0.00169 0.0068 0.5285 0.7528
1.500 0.1328 0.00752 0.00174 0.0082 0.4999 0.7706
1.750 0.1558 0.00761 0.00181 0.0093 0.4736 0.7886
2.000 0.1789 0.00771 0.00188 0.0104 0.4425 0.8071
2.250 0.2019 0.00787 0.00196 0.0115 0.4040 0.8254
2.500 0.2250 0.00808 0.00208 0.0126 0.3630 0.8435
2.750 0.2499 0.00830 0.00221 0.0132 0.3307 0.8602
3.000 0.2764 0.00853 0.00236 0.0134 0.3011 0.8750
3.250 0.3043 0.00878 0.00252 0.0133 0.2699 0.8875
3.500 0.3343 0.00902 0.00269 0.0128 0.2417 0.8990
3.750 0.3685 0.00934 0.00289 0.0113 0.2095 0.9081
4.000 0.4014 0.00968 0.00311 0.0100 0.1793 0.9173
4.250 0.4389 0.01001 0.00335 0.0077 0.1588 0.9238
4.500 0.4718 0.01030 0.00359 0.0065 0.1401 0.9313
4.750 0.5077 0.01071 0.00386 0.0045 0.1095 0.9354
5.000 0.5385 0.01122 0.00420 0.0036 0.0784 0.9413
5.250 0.5674 0.01155 0.00448 0.0033 0.0708 0.9479
5.500 0.5987 0.01187 0.00479 0.0024 0.0659 0.9521
5.750 0.6237 0.01212 0.00507 0.0030 0.0640 0.9599
6.000 0.6556 0.01243 0.00539 0.0020 0.0621 0.9636
6.250 0.6850 0.01275 0.00573 0.0016 0.0604 0.9694
6.500 0.7150 0.01310 0.00610 0.0010 0.0590 0.9749
6.750 0.7469 0.01349 0.00651 -0.0001 0.0573 0.9790
7.000 0.7741 0.01391 0.00695 -0.0001 0.0560 0.9841
7.250 0.8053 0.01437 0.00744 -0.0012 0.0541 0.9865
7.500 0.8368 0.01462 0.00773 -0.0022 0.0532 0.9890
7.750 0.8668 0.01493 0.00809 -0.0029 0.0519 0.9919
8.000 0.8963 0.01526 0.00846 -0.0036 0.0506 0.9944
8.250 0.9275 0.01558 0.00882 -0.0046 0.0491 0.9965
8.500 0.9583 0.01593 0.00918 -0.0056 0.0473 0.9986
8.750 0.9852 0.01637 0.00962 -0.0059 0.0451 1.0000
9.000 0.9987 0.01678 0.01007 -0.0033 0.0438 1.0000
9.250 1.0156 0.01701 0.01035 -0.0013 0.0431 1.0000
9.500 1.0324 0.01725 0.01064 0.0007 0.0418 1.0000
9.750 1.0492 0.01750 0.01093 0.0027 0.0401 1.0000
10.000 1.0654 0.01778 0.01123 0.0048 0.0381 1.0000
10.250 1.0803 0.01813 0.01157 0.0070 0.0363 1.0000
10.500 1.0957 0.01844 0.01194 0.0092 0.0343 1.0000
10.750 1.1108 0.01876 0.01228 0.0114 0.0309 1.0000
11.000 1.1239 0.01915 0.01265 0.0139 0.0257 1.0000
11.250 1.1310 0.01968 0.01312 0.0174 0.0204 1.0000
11.500 1.1355 0.02032 0.01377 0.0213 0.0175 1.0000
11.750 1.1410 0.02101 0.01448 0.0249 0.0158 1.0000
12.000 1.1483 0.02168 0.01521 0.0280 0.0148 1.0000
12.250 1.1561 0.02239 0.01599 0.0309 0.0140 1.0000
12.500 1.1637 0.02317 0.01684 0.0336 0.0134 1.0000
12.750 1.1701 0.02409 0.01783 0.0363 0.0128 1.0000
13.000 1.1760 0.02510 0.01892 0.0388 0.0122 1.0000
13.250 1.1813 0.02622 0.02011 0.0411 0.0117 1.0000
13.500 1.1875 0.02734 0.02135 0.0431 0.0114 1.0000
13.750 1.1935 0.02855 0.02265 0.0448 0.0111 1.0000
14.000 1.1981 0.02994 0.02414 0.0465 0.0107 1.0000
14.250 1.2022 0.03146 0.02576 0.0478 0.0104 1.0000
14.500 1.2053 0.03317 0.02756 0.0489 0.0102 1.0000
14.750 1.2056 0.03525 0.02974 0.0498 0.0098 1.0000
15.000 1.2043 0.03763 0.03223 0.0503 0.0096 1.0000
15.250 1.2036 0.04011 0.03481 0.0505 0.0095 1.0000
15.500 1.1978 0.04329 0.03811 0.0502 0.0093 1.0000
15.750 1.1890 0.04707 0.04202 0.0494 0.0091 1.0000
16.000 1.1811 0.05099 0.04607 0.0482 0.0090 1.0000
16.250 1.1710 0.05543 0.05064 0.0465 0.0089 1.0000
16.500 1.1577 0.06055 0.05591 0.0443 0.0088 1.0000
16.750 1.1459 0.06568 0.06118 0.0419 0.0088 1.0000
17.000 1.1274 0.07217 0.06781 0.0386 0.0088 1.0000
17.250 1.1083 0.07899 0.07480 0.0352 0.0087 1.0000
17.500 1.0855 0.08664 0.08258 0.0312 0.0087 1.0000
17.750 1.0560 0.09558 0.09167 0.0267 0.0089 1.0000
18.000 1.0281 0.10446 0.10069 0.0222 0.0088 1.0000
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