GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 382 AIRFOIL (goe382-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.88 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe382-il-1000000-n5.txt Download as CSV file: xf-goe382-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 382 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6701 0.07749 0.07450 -0.0858 0.8945 0.0218
-16.500 -0.7152 0.06666 0.06343 -0.0932 0.8872 0.0218
-16.250 -0.7442 0.05834 0.05492 -0.0994 0.8790 0.0219
-16.000 -0.7633 0.05164 0.04802 -0.1047 0.8685 0.0219
-15.750 -0.7754 0.04621 0.04240 -0.1091 0.8577 0.0219
-15.500 -0.7824 0.04192 0.03794 -0.1123 0.8461 0.0220
-15.250 -0.7852 0.03839 0.03426 -0.1149 0.8337 0.0220
-15.000 -0.7847 0.03549 0.03121 -0.1168 0.8215 0.0221
-14.750 -0.7818 0.03311 0.02868 -0.1181 0.8081 0.0221
-14.500 -0.7766 0.03114 0.02657 -0.1188 0.7941 0.0222
-14.250 -0.7699 0.02948 0.02479 -0.1189 0.7802 0.0222
-14.000 -0.7614 0.02812 0.02329 -0.1187 0.7657 0.0223
-13.750 -0.7516 0.02696 0.02200 -0.1181 0.7500 0.0223
-13.500 -0.7402 0.02596 0.02086 -0.1172 0.7336 0.0224
-13.250 -0.7277 0.02507 0.01985 -0.1162 0.7179 0.0225
-13.000 -0.7153 0.02432 0.01900 -0.1148 0.7041 0.0226
-12.750 -0.7013 0.02366 0.01822 -0.1134 0.6921 0.0226
-12.500 -0.6839 0.02298 0.01744 -0.1125 0.6810 0.0227
-12.250 -0.6653 0.02235 0.01671 -0.1117 0.6715 0.0228
-12.000 -0.6458 0.02174 0.01601 -0.1109 0.6621 0.0229
-11.750 -0.6255 0.02116 0.01533 -0.1102 0.6539 0.0230
-11.500 -0.6044 0.02059 0.01468 -0.1095 0.6471 0.0231
-11.250 -0.5826 0.02007 0.01408 -0.1089 0.6406 0.0233
-11.000 -0.5601 0.01959 0.01353 -0.1084 0.6349 0.0234
-10.750 -0.5370 0.01912 0.01298 -0.1079 0.6299 0.0236
-10.500 -0.5137 0.01865 0.01244 -0.1074 0.6246 0.0237
-10.250 -0.4903 0.01819 0.01190 -0.1069 0.6194 0.0239
-10.000 -0.4665 0.01773 0.01137 -0.1064 0.6146 0.0240
-9.750 -0.4422 0.01728 0.01087 -0.1060 0.6099 0.0241
-9.500 -0.4177 0.01687 0.01039 -0.1056 0.6048 0.0242
-9.250 -0.3931 0.01649 0.00994 -0.1052 0.6002 0.0244
-9.000 -0.3681 0.01612 0.00952 -0.1048 0.5962 0.0245
-8.750 -0.3425 0.01575 0.00910 -0.1045 0.5935 0.0246
-8.500 -0.3168 0.01540 0.00871 -0.1042 0.5902 0.0247
-8.250 -0.2909 0.01508 0.00835 -0.1039 0.5866 0.0248
-8.000 -0.2649 0.01479 0.00800 -0.1037 0.5830 0.0249
-7.750 -0.2389 0.01451 0.00768 -0.1034 0.5795 0.0250
-7.500 -0.2125 0.01424 0.00737 -0.1032 0.5763 0.0250
-7.250 -0.1873 0.01379 0.00690 -0.1028 0.5736 0.0253
-7.000 -0.1614 0.01344 0.00653 -0.1025 0.5704 0.0254
-6.750 -0.1350 0.01315 0.00621 -0.1023 0.5673 0.0256
-6.500 -0.1084 0.01291 0.00594 -0.1021 0.5638 0.0258
-6.250 -0.0817 0.01270 0.00570 -0.1019 0.5601 0.0260
-6.000 -0.0547 0.01249 0.00547 -0.1018 0.5567 0.0262
-5.750 -0.0273 0.01228 0.00524 -0.1017 0.5539 0.0264
-5.500 0.0001 0.01208 0.00503 -0.1016 0.5507 0.0266
-5.250 0.0274 0.01191 0.00483 -0.1015 0.5469 0.0269
-5.000 0.0546 0.01176 0.00465 -0.1014 0.5426 0.0272
-4.750 0.0819 0.01162 0.00448 -0.1013 0.5386 0.0275
-4.500 0.1098 0.01147 0.00432 -0.1013 0.5356 0.0278
-4.250 0.1376 0.01134 0.00417 -0.1013 0.5318 0.0281
-4.000 0.1652 0.01122 0.00402 -0.1012 0.5273 0.0283
-3.750 0.1925 0.01113 0.00390 -0.1011 0.5223 0.0285
-3.500 0.2202 0.01101 0.00376 -0.1011 0.5181 0.0288
-3.250 0.2477 0.01085 0.00360 -0.1010 0.5135 0.0292
-3.000 0.2751 0.01075 0.00347 -0.1009 0.5083 0.0296
-2.750 0.3021 0.01068 0.00337 -0.1008 0.5028 0.0301
-2.500 0.3300 0.01060 0.00328 -0.1008 0.4976 0.0305
-2.250 0.3574 0.01055 0.00321 -0.1008 0.4909 0.0310
-2.000 0.3845 0.01053 0.00315 -0.1007 0.4848 0.0316
-1.750 0.4123 0.01049 0.00310 -0.1007 0.4795 0.0322
-1.500 0.4396 0.01047 0.00306 -0.1006 0.4730 0.0328
-1.250 0.4663 0.01047 0.00302 -0.1004 0.4665 0.0339
-1.000 0.4936 0.01045 0.00299 -0.1004 0.4601 0.0353
-0.750 0.5202 0.01046 0.00298 -0.1002 0.4530 0.0376
-0.500 0.5467 0.01041 0.00300 -0.1001 0.4476 0.0595
-0.250 0.5740 0.01043 0.00302 -0.1000 0.4422 0.0677
0.000 0.6006 0.01048 0.00306 -0.0999 0.4363 0.0715
0.250 0.6272 0.01054 0.00309 -0.0998 0.4308 0.0740
0.500 0.6542 0.01057 0.00311 -0.0997 0.4256 0.0768
0.750 0.6805 0.01064 0.00316 -0.0995 0.4199 0.0792
1.000 0.7064 0.01071 0.00321 -0.0993 0.4148 0.0821
1.250 0.7333 0.01073 0.00324 -0.0992 0.4112 0.0861
1.500 0.7593 0.01068 0.00330 -0.0991 0.4072 0.1295
1.750 0.7852 0.01075 0.00338 -0.0989 0.4027 0.1447
2.000 0.8103 0.01085 0.00347 -0.0985 0.3978 0.1535
2.250 0.8366 0.01090 0.00354 -0.0984 0.3943 0.1612
2.750 0.8869 0.01077 0.00374 -0.0980 0.3867 0.2878
3.000 0.9113 0.01078 0.00387 -0.0976 0.3829 0.3441
3.250 0.9348 0.01059 0.00401 -0.0973 0.3794 0.4751
3.500 0.9590 0.01044 0.00417 -0.0969 0.3769 0.5888
3.750 0.9828 0.01048 0.00430 -0.0964 0.3736 0.6243
4.000 1.0058 0.01053 0.00445 -0.0957 0.3700 0.6636
4.250 1.0285 0.01060 0.00465 -0.0950 0.3660 0.7160
4.500 1.0507 0.01066 0.00489 -0.0943 0.3622 0.7857
4.750 1.0723 0.01061 0.00512 -0.0932 0.3601 0.8737
5.000 1.0927 0.01068 0.00535 -0.0917 0.3576 0.9476
5.250 1.1285 0.01088 0.00556 -0.0938 0.3544 0.9926
5.500 1.1531 0.01110 0.00576 -0.0937 0.3512 1.0000
5.750 1.1738 0.01136 0.00599 -0.0928 0.3478 1.0000
6.000 1.1949 0.01163 0.00624 -0.0920 0.3446 1.0000
6.250 1.2180 0.01185 0.00646 -0.0915 0.3422 1.0000
6.500 1.2406 0.01209 0.00670 -0.0910 0.3394 1.0000
6.750 1.2625 0.01236 0.00697 -0.0904 0.3366 1.0000
7.000 1.2837 0.01268 0.00728 -0.0898 0.3337 1.0000
7.250 1.3043 0.01303 0.00761 -0.0891 0.3307 1.0000
7.500 1.3246 0.01340 0.00798 -0.0884 0.3279 1.0000
7.750 1.3470 0.01369 0.00829 -0.0880 0.3260 1.0000
8.000 1.3688 0.01401 0.00862 -0.0875 0.3234 1.0000
8.250 1.3894 0.01440 0.00900 -0.0870 0.3205 1.0000
8.500 1.4092 0.01483 0.00944 -0.0863 0.3176 1.0000
8.750 1.4275 0.01534 0.00994 -0.0855 0.3141 1.0000
9.000 1.4459 0.01586 0.01046 -0.0847 0.3105 1.0000
9.250 1.4660 0.01630 0.01091 -0.0842 0.3066 1.0000
9.500 1.4840 0.01687 0.01148 -0.0835 0.3025 1.0000
9.750 1.4999 0.01756 0.01216 -0.0825 0.2983 1.0000
10.000 1.5163 0.01824 0.01285 -0.0817 0.2947 1.0000
10.250 1.5348 0.01881 0.01344 -0.0812 0.2919 1.0000
10.500 1.5517 0.01949 0.01413 -0.0804 0.2877 1.0000
10.750 1.5634 0.02050 0.01512 -0.0793 0.2816 1.0000
11.000 1.5774 0.02139 0.01602 -0.0784 0.2759 1.0000
11.250 1.5896 0.02242 0.01704 -0.0774 0.2693 1.0000
11.500 1.5984 0.02370 0.01830 -0.0761 0.2636 1.0000
11.750 1.6133 0.02460 0.01923 -0.0755 0.2598 1.0000
12.000 1.6249 0.02576 0.02041 -0.0746 0.2551 1.0000
12.250 1.6325 0.02725 0.02189 -0.0735 0.2497 1.0000
12.500 1.6441 0.02846 0.02313 -0.0728 0.2457 1.0000
12.750 1.6537 0.02986 0.02455 -0.0720 0.2409 1.0000
13.000 1.6580 0.03171 0.02640 -0.0709 0.2348 1.0000
13.250 1.6649 0.03339 0.02810 -0.0700 0.2283 1.0000
13.500 1.6652 0.03565 0.03034 -0.0688 0.2204 1.0000
13.750 1.6676 0.03778 0.03249 -0.0678 0.2131 1.0000
14.000 1.6638 0.04050 0.03519 -0.0666 0.2047 1.0000
14.250 1.6631 0.04298 0.03768 -0.0656 0.1962 1.0000
14.500 1.6571 0.04597 0.04065 -0.0644 0.1873 1.0000
14.750 1.6478 0.04933 0.04400 -0.0632 0.1773 1.0000
15.000 1.6379 0.05284 0.04750 -0.0621 0.1670 1.0000
15.250 1.6252 0.05666 0.05131 -0.0610 0.1569 1.0000
15.500 1.6104 0.06079 0.05544 -0.0600 0.1468 1.0000
15.750 1.5957 0.06502 0.05965 -0.0591 0.1373 1.0000
16.000 1.5810 0.06929 0.06392 -0.0583 0.1277 1.0000
16.250 1.5702 0.07328 0.06793 -0.0579 0.1207 1.0000
16.500 1.5569 0.07762 0.07228 -0.0575 0.1145 1.0000
16.750 1.5498 0.08129 0.07599 -0.0573 0.1094 1.0000
17.000 1.5405 0.08526 0.07998 -0.0571 0.1048 1.0000
17.250 1.5334 0.08906 0.08383 -0.0571 0.1014 1.0000
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