GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 500,000 Max Cl/Cd: 92.99 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe442-il-500000-n5.txt Download as CSV file: xf-goe442-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3530 0.10791 0.10556 -0.0228 1.0000 0.0083
-9.500 -0.3503 0.10512 0.10279 -0.0230 1.0000 0.0081
-9.250 -0.3486 0.10219 0.09988 -0.0232 1.0000 0.0080
-9.000 -0.3464 0.09971 0.09743 -0.0232 1.0000 0.0076
-8.750 -0.3469 0.09677 0.09452 -0.0232 1.0000 0.0076
-8.500 -0.3484 0.09399 0.09178 -0.0229 1.0000 0.0075
-8.250 -0.3517 0.09136 0.08919 -0.0223 1.0000 0.0075
-8.000 -0.3513 0.08824 0.08609 -0.0231 0.9993 0.0074
-7.750 -0.3378 0.08379 0.08165 -0.0281 0.9961 0.0075
-7.500 -0.3261 0.07937 0.07724 -0.0331 0.9911 0.0073
-7.250 -0.3064 0.07362 0.07149 -0.0412 0.9869 0.0075
-7.000 -0.2881 0.06795 0.06581 -0.0489 0.9813 0.0077
-6.500 -0.2461 0.01792 0.01366 -0.0940 0.9639 0.0084
-6.250 -0.2221 0.01579 0.01110 -0.0939 0.9585 0.0088
-6.000 -0.1920 0.01462 0.00973 -0.0947 0.9553 0.0093
-5.750 -0.1599 0.01371 0.00864 -0.0957 0.9526 0.0098
-5.500 -0.1344 0.01301 0.00779 -0.0952 0.9462 0.0104
-5.250 -0.1045 0.01236 0.00700 -0.0955 0.9409 0.0113
-5.000 -0.0739 0.01169 0.00616 -0.0960 0.9353 0.0121
-4.750 -0.0464 0.01102 0.00539 -0.0958 0.9269 0.0134
-4.500 -0.0168 0.01058 0.00486 -0.0960 0.9193 0.0147
-4.250 0.0125 0.01017 0.00435 -0.0961 0.9100 0.0163
-4.000 0.0410 0.00981 0.00394 -0.0960 0.8990 0.0190
-3.750 0.0702 0.00958 0.00365 -0.0961 0.8868 0.0222
-3.500 0.0990 0.00934 0.00335 -0.0960 0.8722 0.0254
-3.250 0.1276 0.00927 0.00321 -0.0959 0.8548 0.0293
-3.000 0.1553 0.00913 0.00295 -0.0956 0.8341 0.0322
-2.750 0.1822 0.00909 0.00283 -0.0951 0.8100 0.0354
-2.500 0.2083 0.00909 0.00269 -0.0945 0.7822 0.0384
-2.250 0.2338 0.00913 0.00256 -0.0937 0.7531 0.0404
-2.000 0.2585 0.00901 0.00230 -0.0928 0.7246 0.0437
-1.750 0.2831 0.00903 0.00218 -0.0920 0.6930 0.0463
-1.500 0.3073 0.00907 0.00204 -0.0910 0.6571 0.0485
-1.250 0.3312 0.00914 0.00192 -0.0900 0.6159 0.0506
-1.000 0.3555 0.00924 0.00183 -0.0892 0.5816 0.0524
-0.750 0.3800 0.00928 0.00172 -0.0883 0.5529 0.0558
-0.500 0.4052 0.00934 0.00167 -0.0877 0.5296 0.0606
-0.250 0.4307 0.00941 0.00164 -0.0871 0.5109 0.0646
0.000 0.4567 0.00945 0.00160 -0.0866 0.4964 0.0688
0.250 0.4828 0.00945 0.00157 -0.0861 0.4834 0.0768
0.500 0.5088 0.00946 0.00156 -0.0857 0.4705 0.0911
0.750 0.5338 0.00921 0.00163 -0.0852 0.4592 0.2267
1.000 0.5593 0.00911 0.00170 -0.0848 0.4483 0.3078
1.250 0.5845 0.00898 0.00176 -0.0843 0.4362 0.3982
1.750 0.6578 0.00798 0.00197 -0.0883 0.4044 1.0000
2.000 0.6830 0.00812 0.00203 -0.0877 0.3912 1.0000
2.250 0.7083 0.00827 0.00210 -0.0870 0.3787 1.0000
2.500 0.7334 0.00844 0.00218 -0.0864 0.3648 1.0000
2.750 0.7584 0.00862 0.00228 -0.0858 0.3500 1.0000
3.000 0.7835 0.00880 0.00238 -0.0852 0.3375 1.0000
3.250 0.8086 0.00898 0.00250 -0.0845 0.3263 1.0000
3.500 0.8338 0.00916 0.00263 -0.0840 0.3149 1.0000
3.750 0.8589 0.00934 0.00277 -0.0834 0.3027 1.0000
4.000 0.8839 0.00954 0.00292 -0.0828 0.2897 1.0000
4.250 0.9085 0.00977 0.00309 -0.0821 0.2742 1.0000
4.500 0.9326 0.01006 0.00328 -0.0814 0.2534 1.0000
4.750 0.9559 0.01043 0.00350 -0.0806 0.2242 1.0000
5.000 0.9783 0.01089 0.00380 -0.0797 0.1891 1.0000
5.250 1.0010 0.01134 0.00412 -0.0788 0.1645 1.0000
5.500 1.0243 0.01171 0.00442 -0.0780 0.1504 1.0000
5.750 1.0479 0.01205 0.00472 -0.0773 0.1411 1.0000
6.000 1.0720 0.01233 0.00501 -0.0766 0.1358 1.0000
6.250 1.0958 0.01263 0.00532 -0.0759 0.1312 1.0000
6.500 1.1192 0.01296 0.00565 -0.0751 0.1272 1.0000
6.750 1.1431 0.01323 0.00597 -0.0744 0.1247 1.0000
7.000 1.1669 0.01351 0.00630 -0.0737 0.1223 1.0000
7.250 1.1902 0.01382 0.00665 -0.0730 0.1193 1.0000
7.500 1.2127 0.01420 0.00703 -0.0721 0.1145 1.0000
7.750 1.2356 0.01452 0.00738 -0.0713 0.1095 1.0000
8.000 1.2587 0.01482 0.00773 -0.0706 0.1045 1.0000
8.250 1.2805 0.01522 0.00813 -0.0696 0.0991 1.0000
8.500 1.3034 0.01551 0.00848 -0.0689 0.0944 1.0000
8.750 1.3251 0.01590 0.00885 -0.0679 0.0854 1.0000
9.000 1.3459 0.01635 0.00925 -0.0669 0.0715 1.0000
9.250 1.3586 0.01749 0.01013 -0.0648 0.0375 1.0000
9.500 1.3702 0.01867 0.01122 -0.0624 0.0181 1.0000
9.750 1.3855 0.01950 0.01206 -0.0605 0.0132 1.0000
10.000 1.4018 0.02018 0.01282 -0.0588 0.0110 1.0000
10.250 1.4165 0.02092 0.01363 -0.0569 0.0095 1.0000
10.500 1.4275 0.02179 0.01457 -0.0543 0.0084 1.0000
10.750 1.4401 0.02248 0.01536 -0.0520 0.0079 1.0000
11.000 1.4511 0.02328 0.01626 -0.0496 0.0073 1.0000
11.250 1.4606 0.02417 0.01724 -0.0471 0.0068 1.0000
11.500 1.4687 0.02518 0.01836 -0.0445 0.0064 1.0000
11.750 1.4730 0.02646 0.01975 -0.0416 0.0060 1.0000
12.000 1.4785 0.02769 0.02109 -0.0391 0.0058 1.0000
12.250 1.4847 0.02890 0.02242 -0.0369 0.0055 1.0000
12.500 1.4897 0.03026 0.02389 -0.0348 0.0052 1.0000
12.750 1.4921 0.03190 0.02564 -0.0327 0.0050 1.0000
13.000 1.4946 0.03362 0.02747 -0.0309 0.0048 1.0000
13.250 1.4957 0.03557 0.02954 -0.0294 0.0046 1.0000
13.500 1.4930 0.03805 0.03214 -0.0281 0.0045 1.0000
13.750 1.4893 0.04084 0.03505 -0.0273 0.0043 1.0000
14.000 1.4815 0.04434 0.03870 -0.0270 0.0042 1.0000
14.250 1.4729 0.04829 0.04279 -0.0274 0.0042 1.0000
14.500 1.4622 0.05285 0.04750 -0.0284 0.0041 1.0000
14.750 1.4535 0.05749 0.05231 -0.0298 0.0040 1.0000
15.000 1.4409 0.06296 0.05793 -0.0318 0.0040 1.0000
15.250 1.4312 0.06810 0.06322 -0.0337 0.0040 1.0000
15.500 1.4166 0.07416 0.06943 -0.0362 0.0040 1.0000
15.750 1.4014 0.08046 0.07587 -0.0388 0.0039 1.0000
16.000 1.3869 0.08682 0.08237 -0.0415 0.0039 1.0000
16.250 1.3715 0.09352 0.08920 -0.0446 0.0039 1.0000
16.500 1.3563 0.10035 0.09617 -0.0477 0.0039 1.0000
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