GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.63 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe397-il-1000000-n5.txt Download as CSV file: xf-goe397-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 397 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3983 0.08707 0.08552 -0.0194 1.0000 0.0035
-7.750 -0.3998 0.08420 0.08268 -0.0198 1.0000 0.0036
-7.500 -0.3981 0.08138 0.07988 -0.0207 1.0000 0.0037
-7.250 -0.3829 0.07607 0.07457 -0.0273 0.9855 0.0036
-7.000 -0.3527 0.06950 0.06797 -0.0381 0.9718 0.0043
-6.750 -0.3116 0.05841 0.05676 -0.0559 0.9473 0.0046
-6.500 -0.2831 0.05008 0.04820 -0.0664 0.9033 0.0050
-6.250 -0.2636 0.04646 0.04438 -0.0692 0.8711 0.0054
-6.000 -0.2435 0.03945 0.03709 -0.0739 0.8498 0.0059
-5.750 -0.2234 0.02876 0.02585 -0.0785 0.8352 0.0067
-5.500 -0.2020 0.02321 0.01985 -0.0793 0.8242 0.0073
-5.000 -0.1610 0.01327 0.00881 -0.0785 0.8062 0.0103
-4.750 -0.1363 0.01193 0.00720 -0.0781 0.7980 0.0128
-4.500 -0.1118 0.01044 0.00537 -0.0776 0.7895 0.0161
-4.250 -0.0853 0.01014 0.00495 -0.0774 0.7813 0.0169
-4.000 -0.0579 0.01031 0.00511 -0.0772 0.7722 0.0179
-3.750 -0.0304 0.01061 0.00542 -0.0771 0.7625 0.0186
-3.500 -0.0033 0.01074 0.00551 -0.0769 0.7524 0.0195
-3.250 0.0235 0.01065 0.00535 -0.0767 0.7417 0.0205
-3.000 0.0502 0.01033 0.00492 -0.0764 0.7307 0.0215
-2.750 0.0765 0.01001 0.00447 -0.0761 0.7158 0.0227
-2.500 0.1026 0.00973 0.00403 -0.0757 0.6951 0.0239
-2.250 0.1287 0.00951 0.00367 -0.0753 0.6747 0.0250
-2.000 0.1554 0.00940 0.00348 -0.0750 0.6612 0.0258
-1.750 0.1824 0.00937 0.00337 -0.0748 0.6517 0.0265
-1.500 0.2094 0.00939 0.00334 -0.0746 0.6425 0.0269
-1.250 0.2366 0.00948 0.00339 -0.0745 0.6341 0.0272
-1.000 0.2622 0.00859 0.00238 -0.0740 0.6274 0.0286
-0.750 0.2888 0.00827 0.00204 -0.0738 0.6223 0.0291
-0.500 0.3156 0.00806 0.00179 -0.0735 0.6172 0.0294
-0.250 0.3424 0.00789 0.00159 -0.0733 0.6124 0.0295
0.000 0.3693 0.00772 0.00142 -0.0731 0.6073 0.0298
0.250 0.3961 0.00760 0.00128 -0.0728 0.6026 0.0304
0.500 0.4232 0.00750 0.00116 -0.0726 0.5984 0.0302
0.750 0.4503 0.00740 0.00107 -0.0724 0.5933 0.0299
1.000 0.4773 0.00735 0.00100 -0.0722 0.5876 0.0296
1.250 0.5044 0.00729 0.00094 -0.0720 0.5823 0.0294
1.500 0.5315 0.00724 0.00091 -0.0718 0.5759 0.0292
1.750 0.5580 0.00727 0.00087 -0.0715 0.5571 0.0291
2.000 0.5842 0.00733 0.00085 -0.0712 0.5286 0.0290
2.250 0.6101 0.00744 0.00085 -0.0708 0.4938 0.0291
2.500 0.6351 0.00767 0.00092 -0.0703 0.4492 0.0294
2.750 0.6591 0.00804 0.00105 -0.0697 0.3937 0.0299
3.000 0.6838 0.00835 0.00118 -0.0692 0.3491 0.0321
3.250 0.7091 0.00859 0.00133 -0.0688 0.3167 0.0388
3.750 0.7713 0.00790 0.00210 -0.0719 0.1769 1.0000
4.000 0.7928 0.00858 0.00247 -0.0709 0.1067 1.0000
4.250 0.8156 0.00909 0.00278 -0.0701 0.0614 1.0000
4.500 0.8404 0.00936 0.00300 -0.0695 0.0505 1.0000
4.750 0.8654 0.00959 0.00321 -0.0690 0.0440 1.0000
5.000 0.8903 0.00984 0.00344 -0.0685 0.0377 1.0000
5.250 0.9148 0.01013 0.00370 -0.0680 0.0293 1.0000
5.500 0.9388 0.01048 0.00399 -0.0674 0.0175 1.0000
5.750 0.9630 0.01082 0.00431 -0.0667 0.0112 1.0000
6.000 0.9871 0.01114 0.00466 -0.0661 0.0093 1.0000
6.250 1.0104 0.01158 0.00513 -0.0654 0.0072 1.0000
6.500 1.0342 0.01193 0.00553 -0.0647 0.0065 1.0000
6.750 1.0577 0.01231 0.00595 -0.0640 0.0059 1.0000
7.000 1.0808 0.01274 0.00641 -0.0633 0.0053 1.0000
7.250 1.1021 0.01339 0.00711 -0.0622 0.0045 1.0000
7.500 1.1252 0.01378 0.00755 -0.0615 0.0043 1.0000
7.750 1.1476 0.01424 0.00809 -0.0607 0.0039 1.0000
8.000 1.1692 0.01480 0.00872 -0.0598 0.0036 1.0000
8.250 1.1907 0.01535 0.00932 -0.0589 0.0034 1.0000
8.500 1.2116 0.01595 0.00998 -0.0579 0.0032 1.0000
8.750 1.2312 0.01670 0.01079 -0.0567 0.0030 1.0000
9.000 1.2478 0.01779 0.01200 -0.0551 0.0027 1.0000
9.250 1.2662 0.01864 0.01296 -0.0537 0.0027 1.0000
9.500 1.2849 0.01943 0.01385 -0.0525 0.0026 1.0000
9.750 1.3024 0.02033 0.01487 -0.0510 0.0024 1.0000
10.000 1.3189 0.02132 0.01601 -0.0495 0.0023 1.0000
10.250 1.3347 0.02235 0.01717 -0.0479 0.0022 1.0000
10.500 1.3506 0.02328 0.01821 -0.0464 0.0021 1.0000
10.750 1.3640 0.02445 0.01951 -0.0446 0.0020 1.0000
11.000 1.3790 0.02529 0.02044 -0.0431 0.0019 1.0000
11.250 1.3907 0.02631 0.02157 -0.0411 0.0018 1.0000
11.500 1.3996 0.02731 0.02268 -0.0386 0.0018 1.0000
11.750 1.4050 0.02860 0.02410 -0.0358 0.0017 1.0000
12.000 1.4083 0.03009 0.02573 -0.0331 0.0017 1.0000
12.250 1.4079 0.03200 0.02782 -0.0303 0.0017 1.0000
12.500 1.4087 0.03383 0.02980 -0.0281 0.0016 1.0000
12.750 1.4042 0.03629 0.03245 -0.0259 0.0016 1.0000
13.000 1.3984 0.03908 0.03542 -0.0242 0.0016 1.0000
13.250 1.3787 0.04366 0.04030 -0.0227 0.0015 1.0000
13.500 1.3721 0.04697 0.04377 -0.0222 0.0015 1.0000
13.750 1.3502 0.05257 0.04963 -0.0226 0.0015 1.0000
14.250 1.3205 0.06312 0.06053 -0.0255 0.0015 1.0000
14.750 1.2775 0.07778 0.07555 -0.0323 0.0015 1.0000
15.250 1.2482 0.09268 0.09070 -0.0408 0.0015 1.0000
15.500 1.2252 0.10298 0.10114 -0.0468 0.0016 1.0000
15.750 1.2068 0.11283 0.11109 -0.0524 0.0016 1.0000
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Polar data table (+)
Polar graphs
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