GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 200,000 Max Cl/Cd: 79.97 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe371-il-200000-n5.txt Download as CSV file: xf-goe371-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3223 0.09638 0.09304 -0.0312 1.0000 0.0204
-7.750 -0.3281 0.09438 0.09112 -0.0297 1.0000 0.0204
-7.500 -0.3348 0.09250 0.08932 -0.0281 1.0000 0.0204
-7.250 -0.3172 0.08792 0.08474 -0.0333 0.9953 0.0204
-7.000 -0.2963 0.08314 0.07995 -0.0388 0.9892 0.0203
-6.750 -0.2823 0.07907 0.07589 -0.0385 0.9861 0.0194
-6.500 -0.2607 0.07452 0.07133 -0.0443 0.9787 0.0186
-6.250 -0.2326 0.06944 0.06620 -0.0530 0.9703 0.0194
-6.000 -0.1987 0.06367 0.06036 -0.0631 0.9629 0.0198
-5.750 -0.1702 0.05891 0.05554 -0.0693 0.9547 0.0193
-5.500 -0.1381 0.05365 0.05017 -0.0767 0.9451 0.0191
-5.250 -0.0990 0.04746 0.04378 -0.0855 0.9376 0.0195
-5.000 -0.0681 0.04302 0.03918 -0.0906 0.9269 0.0217
-4.750 -0.0391 0.04018 0.03620 -0.0936 0.9181 0.0232
-4.500 -0.0050 0.03539 0.03111 -0.0978 0.9097 0.0236
-4.250 0.0251 0.03137 0.02676 -0.1001 0.8994 0.0250
-4.000 0.0575 0.02687 0.02169 -0.1019 0.8905 0.0275
-3.750 0.0864 0.02318 0.01737 -0.1027 0.8818 0.0290
-3.500 0.1116 0.02202 0.01615 -0.1031 0.8723 0.0313
-3.250 0.1395 0.02046 0.01427 -0.1033 0.8635 0.0332
-3.000 0.1672 0.01869 0.01209 -0.1031 0.8540 0.0341
-2.750 0.1945 0.01752 0.01059 -0.1028 0.8439 0.0361
-2.500 0.2222 0.01653 0.00926 -0.1025 0.8353 0.0373
-2.250 0.2495 0.01560 0.00806 -0.1022 0.8270 0.0378
-2.000 0.2768 0.01488 0.00713 -0.1018 0.8190 0.0382
-1.750 0.3041 0.01429 0.00636 -0.1015 0.8107 0.0386
-1.500 0.3304 0.01344 0.00540 -0.1011 0.8020 0.0402
-1.250 0.3573 0.01291 0.00480 -0.1008 0.7943 0.0416
-1.000 0.3836 0.01250 0.00434 -0.1003 0.7856 0.0416
-0.750 0.4102 0.01216 0.00394 -0.0999 0.7774 0.0419
-0.500 0.4366 0.01187 0.00361 -0.0994 0.7681 0.0423
-0.250 0.4629 0.01165 0.00335 -0.0989 0.7587 0.0430
0.000 0.4895 0.01149 0.00312 -0.0985 0.7495 0.0440
0.250 0.5159 0.01137 0.00296 -0.0980 0.7394 0.0453
0.500 0.5423 0.01128 0.00282 -0.0976 0.7292 0.0474
0.750 0.5687 0.01123 0.00271 -0.0971 0.7183 0.0501
1.000 0.5950 0.01118 0.00264 -0.0966 0.7062 0.0564
1.250 0.6179 0.01036 0.00278 -0.0960 0.6926 0.3968
1.750 0.6839 0.00931 0.00273 -0.0979 0.6506 1.0000
2.000 0.7083 0.00945 0.00270 -0.0969 0.6197 1.0000
2.250 0.7323 0.00965 0.00270 -0.0960 0.5864 1.0000
2.500 0.7558 0.00990 0.00274 -0.0950 0.5573 1.0000
2.750 0.7794 0.01019 0.00284 -0.0940 0.5332 1.0000
3.000 0.8033 0.01049 0.00300 -0.0932 0.5130 1.0000
3.250 0.8278 0.01076 0.00318 -0.0925 0.4970 1.0000
3.500 0.8525 0.01102 0.00337 -0.0919 0.4843 1.0000
3.750 0.8774 0.01128 0.00358 -0.0913 0.4733 1.0000
4.000 0.9026 0.01151 0.00382 -0.0908 0.4625 1.0000
4.250 0.9275 0.01176 0.00405 -0.0902 0.4514 1.0000
4.500 0.9521 0.01202 0.00430 -0.0896 0.4395 1.0000
4.750 0.9766 0.01229 0.00458 -0.0890 0.4276 1.0000
5.000 1.0010 0.01255 0.00486 -0.0883 0.4143 1.0000
5.250 1.0249 0.01283 0.00514 -0.0876 0.3978 1.0000
5.500 1.0484 0.01311 0.00544 -0.0868 0.3761 1.0000
5.750 1.0710 0.01345 0.00576 -0.0859 0.3486 1.0000
6.000 1.0925 0.01387 0.00609 -0.0849 0.3135 1.0000
6.250 1.1122 0.01445 0.00651 -0.0836 0.2721 1.0000
6.500 1.1311 0.01515 0.00703 -0.0823 0.2378 1.0000
6.750 1.1497 0.01589 0.00765 -0.0809 0.2089 1.0000
7.000 1.1682 0.01664 0.00827 -0.0796 0.1821 1.0000
7.250 1.1878 0.01729 0.00885 -0.0785 0.1580 1.0000
7.500 1.2075 0.01791 0.00944 -0.0773 0.1378 1.0000
7.750 1.2257 0.01867 0.01007 -0.0760 0.1054 1.0000
8.000 1.2408 0.01970 0.01092 -0.0743 0.0722 1.0000
8.250 1.2535 0.02096 0.01199 -0.0722 0.0410 1.0000
8.500 1.2647 0.02233 0.01319 -0.0699 0.0209 1.0000
8.750 1.2788 0.02336 0.01430 -0.0679 0.0177 1.0000
9.000 1.2911 0.02451 0.01560 -0.0656 0.0155 1.0000
9.250 1.3014 0.02562 0.01688 -0.0631 0.0142 1.0000
9.500 1.3115 0.02664 0.01806 -0.0606 0.0132 1.0000
9.750 1.3194 0.02781 0.01938 -0.0579 0.0124 1.0000
10.000 1.3249 0.02916 0.02092 -0.0552 0.0117 1.0000
10.250 1.3292 0.03064 0.02255 -0.0525 0.0113 1.0000
10.500 1.3316 0.03235 0.02439 -0.0499 0.0108 1.0000
10.750 1.3327 0.03424 0.02643 -0.0474 0.0105 1.0000
11.000 1.3323 0.03639 0.02871 -0.0452 0.0102 1.0000
11.250 1.3293 0.03894 0.03139 -0.0431 0.0099 1.0000
11.500 1.3246 0.04193 0.03450 -0.0412 0.0095 1.0000
11.750 1.3300 0.04384 0.03659 -0.0401 0.0090 1.0000
12.000 1.3316 0.04632 0.03923 -0.0389 0.0088 1.0000
12.250 1.3332 0.04884 0.04192 -0.0381 0.0085 1.0000
12.500 1.3332 0.05169 0.04494 -0.0373 0.0083 1.0000
12.750 1.3320 0.05478 0.04820 -0.0367 0.0080 1.0000
13.000 1.3302 0.05804 0.05167 -0.0364 0.0079 1.0000
13.250 1.3270 0.06157 0.05538 -0.0363 0.0077 1.0000
13.500 1.3229 0.06535 0.05934 -0.0365 0.0076 1.0000
13.750 1.3173 0.06945 0.06363 -0.0370 0.0075 1.0000
14.000 1.3107 0.07388 0.06826 -0.0380 0.0075 1.0000
14.250 1.3027 0.07871 0.07328 -0.0394 0.0074 1.0000
14.500 1.2936 0.08391 0.07868 -0.0412 0.0073 1.0000
14.750 1.2836 0.08953 0.08448 -0.0434 0.0073 1.0000
15.000 1.2724 0.09559 0.09074 -0.0462 0.0072 1.0000
15.250 1.2604 0.10205 0.09739 -0.0493 0.0072 1.0000
15.500 1.2475 0.10895 0.10448 -0.0529 0.0072 1.0000
15.750 1.2339 0.11629 0.11201 -0.0570 0.0072 1.0000
16.000 1.2196 0.12413 0.12003 -0.0615 0.0072 1.0000
16.250 1.2042 0.13264 0.12873 -0.0666 0.0073 1.0000
16.500 1.1881 0.14189 0.13815 -0.0724 0.0074 1.0000
16.750 1.1711 0.15207 0.14850 -0.0788 0.0075 1.0000
17.000 1.1520 0.16359 0.16018 -0.0860 0.0077 1.0000
17.250 1.1305 0.17674 0.17342 -0.0940 0.0079 1.0000
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