GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.74 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe621-il-1000000.txt Download as CSV file: xf-goe621-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7425 0.05397 0.05128 -0.1023 0.9959 0.0276
-14.500 -0.7622 0.04554 0.04265 -0.1118 0.9892 0.0277
-14.250 -0.7641 0.03905 0.03598 -0.1210 0.9849 0.0278
-14.000 -0.7525 0.03346 0.03020 -0.1313 0.9819 0.0281
-13.750 -0.7387 0.02964 0.02619 -0.1387 0.9769 0.0282
-13.500 -0.7191 0.02734 0.02373 -0.1428 0.9724 0.0285
-13.250 -0.6987 0.02568 0.02193 -0.1450 0.9671 0.0287
-13.000 -0.6901 0.02461 0.02073 -0.1436 0.9580 0.0289
-12.750 -0.6808 0.02369 0.01969 -0.1420 0.9505 0.0291
-12.500 -0.6691 0.02302 0.01892 -0.1401 0.9433 0.0293
-12.250 -0.6544 0.02244 0.01822 -0.1386 0.9372 0.0295
-12.000 -0.6410 0.02180 0.01749 -0.1367 0.9304 0.0296
-11.750 -0.6323 0.02035 0.01588 -0.1346 0.9238 0.0298
-11.500 -0.6203 0.01924 0.01470 -0.1326 0.9175 0.0302
-11.250 -0.6038 0.01845 0.01385 -0.1311 0.9114 0.0305
-11.000 -0.5842 0.01785 0.01319 -0.1299 0.9060 0.0307
-10.750 -0.5643 0.01733 0.01263 -0.1287 0.8998 0.0310
-10.500 -0.5433 0.01683 0.01207 -0.1277 0.8934 0.0313
-10.250 -0.5218 0.01634 0.01151 -0.1267 0.8870 0.0316
-10.000 -0.5001 0.01585 0.01096 -0.1257 0.8795 0.0319
-9.750 -0.4778 0.01538 0.01040 -0.1248 0.8724 0.0323
-9.500 -0.4552 0.01492 0.00989 -0.1239 0.8644 0.0326
-9.250 -0.4319 0.01453 0.00941 -0.1230 0.8561 0.0330
-9.000 -0.4080 0.01418 0.00900 -0.1223 0.8469 0.0334
-8.750 -0.3843 0.01383 0.00855 -0.1214 0.8371 0.0336
-8.500 -0.3600 0.01352 0.00817 -0.1207 0.8260 0.0339
-8.250 -0.3383 0.01293 0.00748 -0.1196 0.8147 0.0343
-8.000 -0.3165 0.01241 0.00688 -0.1185 0.8029 0.0349
-7.750 -0.2925 0.01206 0.00648 -0.1178 0.7915 0.0354
-7.500 -0.2679 0.01180 0.00615 -0.1171 0.7810 0.0359
-7.250 -0.2431 0.01156 0.00584 -0.1164 0.7704 0.0364
-7.000 -0.2178 0.01132 0.00555 -0.1158 0.7611 0.0370
-6.750 -0.1926 0.01112 0.00527 -0.1151 0.7520 0.0376
-6.500 -0.1666 0.01092 0.00501 -0.1146 0.7445 0.0381
-6.250 -0.1405 0.01076 0.00479 -0.1142 0.7372 0.0386
-6.000 -0.1157 0.01044 0.00441 -0.1135 0.7308 0.0396
-5.750 -0.0897 0.01019 0.00414 -0.1130 0.7245 0.0407
-5.500 -0.0637 0.01003 0.00393 -0.1125 0.7179 0.0416
-5.250 -0.0370 0.00988 0.00374 -0.1121 0.7120 0.0427
-5.000 -0.0101 0.00974 0.00357 -0.1118 0.7058 0.0437
-4.750 0.0157 0.00956 0.00332 -0.1112 0.6991 0.0453
-4.500 0.0424 0.00937 0.00314 -0.1108 0.6938 0.0472
-4.250 0.0696 0.00924 0.00299 -0.1105 0.6886 0.0493
-4.000 0.0960 0.00909 0.00280 -0.1101 0.6831 0.0523
-3.750 0.1228 0.00896 0.00266 -0.1097 0.6778 0.0562
-3.500 0.1498 0.00877 0.00250 -0.1094 0.6733 0.0636
-3.250 0.1762 0.00857 0.00238 -0.1090 0.6682 0.0808
-3.000 0.2025 0.00846 0.00231 -0.1085 0.6627 0.0996
-2.750 0.2299 0.00835 0.00224 -0.1083 0.6581 0.1107
-2.500 0.2574 0.00827 0.00217 -0.1080 0.6531 0.1193
-2.250 0.2842 0.00820 0.00211 -0.1077 0.6478 0.1292
-2.000 0.3110 0.00813 0.00205 -0.1073 0.6424 0.1414
-1.750 0.3382 0.00801 0.00200 -0.1071 0.6375 0.1586
-1.500 0.3648 0.00788 0.00195 -0.1067 0.6326 0.1852
-1.250 0.3911 0.00780 0.00193 -0.1063 0.6278 0.2143
-1.000 0.4180 0.00770 0.00192 -0.1060 0.6237 0.2436
-0.750 0.4451 0.00761 0.00191 -0.1057 0.6191 0.2707
-0.500 0.4718 0.00756 0.00192 -0.1053 0.6138 0.2949
-0.250 0.4980 0.00756 0.00193 -0.1049 0.6082 0.3178
0.000 0.5254 0.00750 0.00195 -0.1046 0.6035 0.3385
0.250 0.5523 0.00748 0.00196 -0.1043 0.5980 0.3570
0.500 0.5783 0.00750 0.00198 -0.1038 0.5920 0.3734
0.750 0.6054 0.00748 0.00201 -0.1035 0.5864 0.3885
1.000 0.6317 0.00748 0.00203 -0.1031 0.5790 0.4034
1.250 0.6575 0.00751 0.00206 -0.1025 0.5722 0.4190
1.500 0.6840 0.00751 0.00209 -0.1021 0.5644 0.4360
1.750 0.7087 0.00755 0.00214 -0.1014 0.5555 0.4557
2.000 0.7341 0.00754 0.00218 -0.1008 0.5453 0.4812
2.250 0.7581 0.00756 0.00224 -0.0999 0.5341 0.5121
2.500 0.7805 0.00756 0.00232 -0.0988 0.5201 0.5556
2.750 0.7962 0.00731 0.00244 -0.0963 0.5033 0.7093
3.000 0.8850 0.00733 0.00285 -0.1095 0.4600 0.9901
3.250 0.9263 0.00793 0.00315 -0.1128 0.4085 1.0000
3.500 0.9404 0.00833 0.00337 -0.1101 0.3777 1.0000
3.750 0.9563 0.00866 0.00357 -0.1078 0.3566 1.0000
4.000 0.9742 0.00891 0.00374 -0.1058 0.3432 1.0000
4.250 0.9920 0.00916 0.00391 -0.1038 0.3323 1.0000
4.500 1.0107 0.00937 0.00407 -0.1019 0.3237 1.0000
4.750 1.0286 0.00960 0.00425 -0.0999 0.3157 1.0000
5.000 1.0478 0.00977 0.00440 -0.0982 0.3098 1.0000
5.250 1.0630 0.00999 0.00458 -0.0957 0.3038 1.0000
5.500 1.0790 0.01017 0.00474 -0.0933 0.2988 1.0000
5.750 1.0968 0.01034 0.00490 -0.0913 0.2943 1.0000
6.000 1.1137 0.01055 0.00509 -0.0892 0.2894 1.0000
6.250 1.1297 0.01082 0.00533 -0.0870 0.2839 1.0000
6.500 1.1497 0.01099 0.00551 -0.0855 0.2805 1.0000
6.750 1.1689 0.01120 0.00571 -0.0839 0.2761 1.0000
7.000 1.1869 0.01147 0.00596 -0.0822 0.2713 1.0000
7.250 1.2042 0.01178 0.00625 -0.0804 0.2662 1.0000
7.500 1.2250 0.01198 0.00646 -0.0792 0.2624 1.0000
7.750 1.2438 0.01226 0.00673 -0.0778 0.2574 1.0000
8.000 1.2610 0.01262 0.00706 -0.0761 0.2518 1.0000
8.250 1.2805 0.01290 0.00735 -0.0748 0.2479 1.0000
8.500 1.2999 0.01320 0.00765 -0.0736 0.2433 1.0000
8.750 1.3176 0.01358 0.00802 -0.0721 0.2379 1.0000
9.000 1.3351 0.01398 0.00841 -0.0706 0.2329 1.0000
9.250 1.3544 0.01431 0.00876 -0.0695 0.2282 1.0000
9.500 1.3708 0.01479 0.00920 -0.0679 0.2216 1.0000
9.750 1.3881 0.01524 0.00966 -0.0666 0.2162 1.0000
10.000 1.4051 0.01572 0.01012 -0.0652 0.2093 1.0000
10.250 1.4197 0.01633 0.01069 -0.0636 0.2015 1.0000
10.500 1.4359 0.01688 0.01124 -0.0623 0.1946 1.0000
10.750 1.4496 0.01759 0.01191 -0.0607 0.1873 1.0000
11.000 1.4649 0.01821 0.01253 -0.0593 0.1807 1.0000
11.250 1.4769 0.01905 0.01333 -0.0576 0.1723 1.0000
11.500 1.4911 0.01978 0.01405 -0.0563 0.1662 1.0000
11.750 1.5023 0.02071 0.01496 -0.0547 0.1596 1.0000
12.000 1.5168 0.02147 0.01573 -0.0534 0.1549 1.0000
12.250 1.5280 0.02245 0.01670 -0.0520 0.1496 1.0000
12.500 1.5403 0.02339 0.01764 -0.0507 0.1449 1.0000
12.750 1.5535 0.02428 0.01856 -0.0495 0.1416 1.0000
13.000 1.5630 0.02545 0.01972 -0.0481 0.1365 1.0000
13.250 1.5742 0.02653 0.02081 -0.0469 0.1327 1.0000
13.500 1.5869 0.02754 0.02186 -0.0459 0.1299 1.0000
13.750 1.5984 0.02866 0.02300 -0.0449 0.1270 1.0000
14.000 1.6075 0.02997 0.02432 -0.0437 0.1237 1.0000
14.250 1.6163 0.03134 0.02571 -0.0426 0.1207 1.0000
14.500 1.6291 0.03240 0.02682 -0.0418 0.1187 1.0000
14.750 1.6396 0.03369 0.02815 -0.0410 0.1163 1.0000
15.000 1.6476 0.03518 0.02965 -0.0400 0.1130 1.0000
15.250 1.6533 0.03689 0.03138 -0.0390 0.1097 1.0000
15.500 1.6641 0.03819 0.03273 -0.0383 0.1077 1.0000
15.750 1.6736 0.03963 0.03422 -0.0376 0.1053 1.0000
16.000 1.6793 0.04142 0.03602 -0.0368 0.1017 1.0000
16.250 1.6829 0.04341 0.03802 -0.0359 0.0979 1.0000
16.500 1.6916 0.04498 0.03965 -0.0353 0.0949 1.0000
16.750 1.6937 0.04717 0.04183 -0.0346 0.0896 1.0000
17.000 1.6970 0.04932 0.04400 -0.0340 0.0848 1.0000
17.250 1.6892 0.05258 0.04720 -0.0331 0.0729 1.0000
17.500 1.6724 0.05686 0.05141 -0.0323 0.0594 1.0000
17.750 1.6503 0.06192 0.05642 -0.0317 0.0467 1.0000
18.000 1.6183 0.06833 0.06280 -0.0314 0.0333 1.0000
18.250 1.6001 0.07337 0.06788 -0.0315 0.0272 1.0000
18.500 1.5800 0.07882 0.07337 -0.0319 0.0222 1.0000
18.750 1.5659 0.08363 0.07826 -0.0324 0.0201 1.0000
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Polar data table (+)
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