GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 200,000 Max Cl/Cd: 70.1 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe490-il-200000-n5.txt Download as CSV file: xf-goe490-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 490 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3910 0.08749 0.08405 -0.0320 1.0000 0.0180
-8.500 -0.4003 0.08367 0.08030 -0.0323 1.0000 0.0182
-8.250 -0.4123 0.08043 0.07714 -0.0319 1.0000 0.0182
-8.000 -0.4307 0.07743 0.07423 -0.0306 1.0000 0.0184
-7.750 -0.4461 0.07312 0.07001 -0.0312 1.0000 0.0187
-7.500 -0.4561 0.06538 0.06229 -0.0367 0.9979 0.0192
-7.250 -0.4382 0.05588 0.05266 -0.0480 0.9906 0.0203
-6.750 -0.4071 0.03141 0.02697 -0.0650 0.9753 0.0230
-6.500 -0.3872 0.02697 0.02183 -0.0660 0.9683 0.0253
-6.250 -0.3570 0.02474 0.01898 -0.0674 0.9647 0.0276
-6.000 -0.3359 0.02237 0.01627 -0.0671 0.9577 0.0295
-5.750 -0.3045 0.02167 0.01547 -0.0683 0.9538 0.0320
-5.500 -0.2759 0.02057 0.01410 -0.0687 0.9488 0.0344
-5.250 -0.2472 0.01950 0.01272 -0.0689 0.9429 0.0365
-5.000 -0.2133 0.01851 0.01144 -0.0702 0.9390 0.0383
-4.750 -0.1858 0.01716 0.00991 -0.0702 0.9319 0.0402
-4.500 -0.1525 0.01637 0.00903 -0.0713 0.9262 0.0424
-4.250 -0.1179 0.01568 0.00822 -0.0727 0.9206 0.0447
-4.000 -0.0861 0.01498 0.00740 -0.0733 0.9127 0.0462
-3.750 -0.0503 0.01433 0.00660 -0.0747 0.9064 0.0478
-3.500 -0.0181 0.01381 0.00598 -0.0754 0.8969 0.0492
-3.250 0.0144 0.01328 0.00538 -0.0763 0.8882 0.0512
-3.000 0.0479 0.01283 0.00488 -0.0773 0.8801 0.0547
-2.750 0.0781 0.01250 0.00451 -0.0776 0.8702 0.0601
-2.500 0.1097 0.01213 0.00416 -0.0783 0.8606 0.0693
-2.250 0.1408 0.01183 0.00388 -0.0788 0.8501 0.0899
-2.000 0.1696 0.01164 0.00373 -0.0788 0.8381 0.1145
-1.750 0.1985 0.01152 0.00356 -0.0788 0.8260 0.1300
-1.500 0.2270 0.01139 0.00339 -0.0788 0.8131 0.1430
-1.250 0.2550 0.01127 0.00325 -0.0787 0.7998 0.1578
-1.000 0.2823 0.01114 0.00312 -0.0784 0.7861 0.1742
-0.750 0.3090 0.01102 0.00304 -0.0780 0.7719 0.1957
-0.500 0.3354 0.01093 0.00302 -0.0776 0.7572 0.2286
-0.250 0.3616 0.01088 0.00298 -0.0770 0.7418 0.2597
0.000 0.3874 0.01085 0.00291 -0.0764 0.7262 0.2827
0.250 0.4127 0.01081 0.00284 -0.0757 0.7100 0.3054
0.500 0.4372 0.01074 0.00278 -0.0749 0.6925 0.3313
0.750 0.4600 0.01059 0.00272 -0.0738 0.6715 0.3828
1.250 0.5895 0.00966 0.00288 -0.0893 0.6133 1.0000
1.500 0.6118 0.00982 0.00291 -0.0881 0.5925 1.0000
1.750 0.6339 0.00999 0.00296 -0.0867 0.5712 1.0000
2.000 0.6556 0.01018 0.00303 -0.0854 0.5489 1.0000
2.250 0.6769 0.01040 0.00310 -0.0839 0.5256 1.0000
2.500 0.6978 0.01064 0.00320 -0.0824 0.5010 1.0000
2.750 0.7185 0.01090 0.00332 -0.0809 0.4785 1.0000
3.000 0.7393 0.01117 0.00345 -0.0794 0.4570 1.0000
3.250 0.7605 0.01143 0.00362 -0.0780 0.4391 1.0000
3.500 0.7823 0.01168 0.00380 -0.0768 0.4250 1.0000
3.750 0.8045 0.01191 0.00399 -0.0756 0.4132 1.0000
4.000 0.8266 0.01214 0.00420 -0.0744 0.4018 1.0000
4.250 0.8485 0.01239 0.00441 -0.0732 0.3900 1.0000
4.500 0.8707 0.01262 0.00464 -0.0721 0.3775 1.0000
4.750 0.8928 0.01285 0.00487 -0.0709 0.3648 1.0000
5.000 0.9146 0.01310 0.00513 -0.0697 0.3513 1.0000
5.250 0.9361 0.01336 0.00539 -0.0684 0.3372 1.0000
5.500 0.9569 0.01365 0.00565 -0.0671 0.3198 1.0000
5.750 0.9748 0.01407 0.00592 -0.0653 0.2881 1.0000
6.000 0.9919 0.01458 0.00627 -0.0634 0.2547 1.0000
6.250 1.0100 0.01507 0.00666 -0.0617 0.2312 1.0000
6.500 1.0277 0.01560 0.00707 -0.0599 0.2066 1.0000
6.750 1.0459 0.01611 0.00750 -0.0583 0.1865 1.0000
7.000 1.0637 0.01665 0.00795 -0.0566 0.1630 1.0000
7.250 1.0800 0.01731 0.00848 -0.0548 0.1363 1.0000
7.500 1.0947 0.01808 0.00908 -0.0527 0.1079 1.0000
7.750 1.1029 0.01936 0.00999 -0.0497 0.0513 1.0000
8.000 1.1102 0.02070 0.01113 -0.0465 0.0205 1.0000
8.250 1.1254 0.02140 0.01192 -0.0444 0.0181 1.0000
8.500 1.1390 0.02217 0.01281 -0.0421 0.0164 1.0000
8.750 1.1509 0.02296 0.01373 -0.0395 0.0155 1.0000
9.000 1.1608 0.02387 0.01482 -0.0366 0.0145 1.0000
9.250 1.1677 0.02496 0.01609 -0.0335 0.0137 1.0000
9.500 1.1760 0.02594 0.01721 -0.0307 0.0131 1.0000
9.750 1.1844 0.02693 0.01833 -0.0281 0.0124 1.0000
10.000 1.1898 0.02813 0.01967 -0.0253 0.0118 1.0000
10.250 1.1938 0.02945 0.02113 -0.0225 0.0116 1.0000
10.500 1.1960 0.03095 0.02276 -0.0199 0.0113 1.0000
10.750 1.1971 0.03262 0.02455 -0.0175 0.0111 1.0000
11.000 1.1968 0.03450 0.02655 -0.0153 0.0109 1.0000
11.250 1.1958 0.03658 0.02874 -0.0134 0.0106 1.0000
11.500 1.1953 0.03877 0.03104 -0.0118 0.0105 1.0000
11.750 1.1935 0.04123 0.03364 -0.0105 0.0103 1.0000
12.000 1.1923 0.04378 0.03629 -0.0095 0.0101 1.0000
12.250 1.1909 0.04646 0.03906 -0.0087 0.0099 1.0000
12.500 1.1891 0.04931 0.04199 -0.0080 0.0097 1.0000
12.750 1.1880 0.05216 0.04490 -0.0074 0.0095 1.0000
13.000 1.1881 0.05500 0.04779 -0.0067 0.0093 1.0000
13.250 1.1896 0.05781 0.05066 -0.0059 0.0090 1.0000
13.500 1.1885 0.06086 0.05392 -0.0065 0.0087 1.0000
13.750 1.1885 0.06394 0.05716 -0.0066 0.0085 1.0000
14.000 1.1886 0.06710 0.06045 -0.0068 0.0085 1.0000
14.250 1.1870 0.07054 0.06405 -0.0073 0.0083 1.0000
14.500 1.1848 0.07419 0.06786 -0.0079 0.0082 1.0000
14.750 1.1816 0.07810 0.07194 -0.0088 0.0081 1.0000
15.000 1.1773 0.08226 0.07626 -0.0100 0.0081 1.0000
15.250 1.1712 0.08685 0.08102 -0.0115 0.0080 1.0000
15.500 1.1648 0.09161 0.08596 -0.0133 0.0080 1.0000
15.750 1.1570 0.09677 0.09129 -0.0154 0.0079 1.0000
16.000 1.1485 0.10217 0.09686 -0.0179 0.0079 1.0000
16.250 1.1390 0.10795 0.10281 -0.0207 0.0079 1.0000
16.500 1.1277 0.11428 0.10932 -0.0240 0.0079 1.0000
16.750 1.1166 0.12079 0.11600 -0.0276 0.0079 1.0000
17.000 1.1055 0.12749 0.12286 -0.0314 0.0079 1.0000
17.250 1.0952 0.13417 0.12969 -0.0353 0.0080 1.0000
17.500 1.0829 0.14168 0.13735 -0.0398 0.0080 1.0000
17.750 1.0709 0.14942 0.14524 -0.0445 0.0080 1.0000
18.000 1.0585 0.15757 0.15352 -0.0495 0.0081 1.0000
18.250 1.0456 0.16624 0.16232 -0.0549 0.0082 1.0000
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