GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 500,000 Max Cl/Cd: 102.1 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe397-il-500000-n5.txt Download as CSV file: xf-goe397-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3866 0.08950 0.08729 -0.0198 1.0000 0.0065
-7.750 -0.3869 0.08631 0.08414 -0.0205 1.0000 0.0068
-7.500 -0.3883 0.08357 0.08144 -0.0208 1.0000 0.0068
-7.250 -0.3844 0.08058 0.07847 -0.0223 1.0000 0.0067
-7.000 -0.3795 0.07707 0.07500 -0.0245 1.0000 0.0067
-6.750 -0.3682 0.07305 0.07099 -0.0283 0.9979 0.0067
-6.500 -0.3431 0.06751 0.06539 -0.0363 0.9865 0.0067
-6.250 -0.3119 0.06066 0.05848 -0.0461 0.9752 0.0069
-6.000 -0.2769 0.05357 0.05129 -0.0562 0.9615 0.0071
-5.750 -0.2419 0.04977 0.04739 -0.0627 0.9478 0.0078
-5.500 -0.2064 0.04535 0.04283 -0.0690 0.9301 0.0087
-5.250 -0.1734 0.03841 0.03561 -0.0752 0.9074 0.0097
-5.000 -0.1457 0.02959 0.02628 -0.0793 0.8855 0.0109
-4.750 -0.1208 0.02741 0.02387 -0.0798 0.8686 0.0117
-4.500 -0.1002 0.01635 0.01159 -0.0798 0.8549 0.0167
-4.000 -0.0481 0.01653 0.01163 -0.0794 0.8314 0.0185
-3.750 -0.0218 0.01690 0.01195 -0.0792 0.8211 0.0199
-3.500 0.0039 0.01595 0.01076 -0.0788 0.8117 0.0219
-3.250 0.0297 0.01490 0.00943 -0.0784 0.8022 0.0240
-3.000 0.0560 0.01419 0.00850 -0.0780 0.7927 0.0255
-2.750 0.0822 0.01352 0.00759 -0.0776 0.7833 0.0262
-2.500 0.1089 0.01335 0.00729 -0.0773 0.7736 0.0269
-2.250 0.1354 0.01273 0.00648 -0.0770 0.7644 0.0274
-2.000 0.1606 0.01114 0.00464 -0.0765 0.7541 0.0291
-1.750 0.1866 0.01068 0.00406 -0.0761 0.7394 0.0303
-1.500 0.2126 0.01037 0.00364 -0.0757 0.7222 0.0315
-1.250 0.2387 0.01008 0.00325 -0.0753 0.7067 0.0324
-1.000 0.2649 0.00982 0.00289 -0.0749 0.6934 0.0331
-0.750 0.2911 0.00958 0.00257 -0.0745 0.6811 0.0335
-0.500 0.3173 0.00938 0.00229 -0.0741 0.6711 0.0340
-0.250 0.3439 0.00922 0.00210 -0.0738 0.6627 0.0350
0.000 0.3704 0.00904 0.00188 -0.0735 0.6554 0.0352
0.250 0.3969 0.00887 0.00168 -0.0731 0.6484 0.0349
0.500 0.4235 0.00875 0.00152 -0.0728 0.6422 0.0347
0.750 0.4503 0.00863 0.00140 -0.0726 0.6355 0.0345
1.250 0.5039 0.00851 0.00125 -0.0720 0.6231 0.0344
1.500 0.5307 0.00848 0.00122 -0.0718 0.6172 0.0344
1.750 0.5576 0.00847 0.00120 -0.0716 0.6112 0.0346
2.000 0.5844 0.00848 0.00120 -0.0713 0.6034 0.0351
2.250 0.6107 0.00852 0.00122 -0.0709 0.5882 0.0360
2.500 0.6369 0.00857 0.00125 -0.0706 0.5716 0.0383
3.000 0.7055 0.00691 0.00157 -0.0742 0.5151 1.0000
3.250 0.7275 0.00736 0.00171 -0.0732 0.4432 1.0000
3.500 0.7497 0.00789 0.00195 -0.0722 0.3846 1.0000
3.750 0.7738 0.00824 0.00217 -0.0716 0.3497 1.0000
4.000 0.7977 0.00861 0.00241 -0.0709 0.3151 1.0000
4.250 0.8208 0.00908 0.00270 -0.0702 0.2633 1.0000
4.500 0.8369 0.01044 0.00336 -0.0686 0.1159 1.0000
4.750 0.8585 0.01113 0.00380 -0.0677 0.0665 1.0000
5.000 0.8825 0.01151 0.00413 -0.0671 0.0542 1.0000
5.250 0.9069 0.01182 0.00446 -0.0665 0.0461 1.0000
5.500 0.9309 0.01218 0.00481 -0.0659 0.0380 1.0000
5.750 0.9545 0.01258 0.00518 -0.0653 0.0258 1.0000
6.000 0.9773 0.01309 0.00563 -0.0645 0.0159 1.0000
6.250 0.9994 0.01371 0.00631 -0.0634 0.0113 1.0000
6.500 1.0224 0.01417 0.00687 -0.0626 0.0100 1.0000
6.750 1.0447 0.01469 0.00746 -0.0618 0.0086 1.0000
7.000 1.0657 0.01538 0.00822 -0.0607 0.0077 1.0000
7.250 1.0846 0.01634 0.00929 -0.0593 0.0069 1.0000
7.500 1.1047 0.01710 0.01017 -0.0580 0.0065 1.0000
7.750 1.1244 0.01791 0.01108 -0.0568 0.0060 1.0000
8.000 1.1442 0.01868 0.01196 -0.0556 0.0055 1.0000
8.250 1.1644 0.01934 0.01266 -0.0547 0.0050 1.0000
8.500 1.1807 0.02051 0.01392 -0.0531 0.0046 1.0000
8.750 1.1955 0.02197 0.01553 -0.0512 0.0044 1.0000
9.000 1.2128 0.02309 0.01682 -0.0497 0.0042 1.0000
9.250 1.2281 0.02456 0.01848 -0.0480 0.0041 1.0000
9.500 1.2428 0.02613 0.02025 -0.0463 0.0039 1.0000
9.750 1.2562 0.02786 0.02221 -0.0444 0.0037 1.0000
10.000 1.2678 0.02977 0.02435 -0.0425 0.0035 1.0000
10.250 1.2763 0.03204 0.02689 -0.0402 0.0034 1.0000
10.500 1.2815 0.03437 0.02950 -0.0376 0.0033 1.0000
10.750 1.2817 0.03661 0.03203 -0.0344 0.0033 1.0000
11.000 1.2769 0.03923 0.03492 -0.0310 0.0032 1.0000
11.250 1.2688 0.04214 0.03809 -0.0280 0.0032 1.0000
11.500 1.2645 0.04443 0.04055 -0.0259 0.0031 1.0000
11.750 1.2559 0.04745 0.04377 -0.0243 0.0031 1.0000
12.000 1.2458 0.05085 0.04736 -0.0234 0.0030 1.0000
12.250 1.2133 0.05810 0.05499 -0.0234 0.0031 1.0000
12.500 1.2031 0.06224 0.05928 -0.0244 0.0031 1.0000
12.750 1.1947 0.06641 0.06356 -0.0260 0.0030 1.0000
13.000 1.1406 0.08002 0.07757 -0.0322 0.0032 1.0000
13.250 1.1111 0.09070 0.08839 -0.0388 0.0032 1.0000
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Polar data table (+)
Polar graphs
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