GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 500,000 Max Cl/Cd: 103.47 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe723-il-500000-n5.txt Download as CSV file: xf-goe723-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3471 0.10115 0.09864 -0.0414 1.0000 0.0216
-10.250 -0.3497 0.09713 0.09463 -0.0425 1.0000 0.0217
-9.750 -0.5089 0.03963 0.03652 -0.0981 0.9540 0.0232
-9.500 -0.4864 0.03420 0.03072 -0.1069 0.9388 0.0233
-9.250 -0.4505 0.03105 0.02731 -0.1134 0.9275 0.0236
-9.000 -0.4124 0.02898 0.02503 -0.1186 0.9135 0.0239
-8.750 -0.3806 0.02737 0.02320 -0.1215 0.8955 0.0242
-8.500 -0.3579 0.02578 0.02135 -0.1224 0.8760 0.0244
-8.250 -0.3385 0.02431 0.01962 -0.1222 0.8577 0.0247
-8.000 -0.3199 0.02288 0.01791 -0.1216 0.8413 0.0248
-7.750 -0.3004 0.02166 0.01644 -0.1208 0.8263 0.0250
-7.500 -0.2802 0.02058 0.01512 -0.1200 0.8120 0.0253
-7.000 -0.2376 0.01864 0.01274 -0.1183 0.7863 0.0257
-6.750 -0.2152 0.01780 0.01171 -0.1175 0.7754 0.0259
-6.250 -0.1688 0.01641 0.00998 -0.1160 0.7545 0.0264
-6.000 -0.1447 0.01589 0.00929 -0.1153 0.7455 0.0268
-5.750 -0.1201 0.01541 0.00868 -0.1147 0.7369 0.0271
-5.500 -0.0956 0.01490 0.00805 -0.1140 0.7290 0.0272
-5.250 -0.0707 0.01444 0.00749 -0.1134 0.7208 0.0274
-5.000 -0.0457 0.01406 0.00700 -0.1128 0.7133 0.0275
-4.750 -0.0216 0.01336 0.00624 -0.1121 0.7061 0.0278
-4.500 0.0030 0.01288 0.00570 -0.1114 0.6994 0.0281
-4.250 0.0281 0.01249 0.00528 -0.1109 0.6930 0.0285
-4.000 0.0534 0.01215 0.00490 -0.1103 0.6861 0.0287
-3.750 0.0787 0.01187 0.00456 -0.1097 0.6797 0.0290
-3.500 0.1045 0.01159 0.00426 -0.1092 0.6734 0.0294
-3.250 0.1302 0.01135 0.00398 -0.1087 0.6673 0.0298
-3.000 0.1560 0.01113 0.00372 -0.1082 0.6615 0.0301
-2.750 0.1822 0.01092 0.00348 -0.1077 0.6552 0.0306
-2.500 0.2082 0.01075 0.00327 -0.1072 0.6490 0.0313
-2.250 0.2345 0.01059 0.00307 -0.1067 0.6436 0.0319
-2.000 0.2609 0.01044 0.00289 -0.1063 0.6374 0.0324
-1.750 0.2871 0.01032 0.00272 -0.1058 0.6314 0.0328
-1.500 0.3134 0.01014 0.00252 -0.1054 0.6255 0.0334
-1.250 0.3396 0.01001 0.00235 -0.1049 0.6179 0.0343
-1.000 0.3657 0.00993 0.00223 -0.1044 0.6097 0.0353
-0.750 0.3920 0.00986 0.00213 -0.1039 0.6010 0.0364
-0.500 0.4184 0.00982 0.00205 -0.1034 0.5945 0.0376
-0.250 0.4452 0.00977 0.00198 -0.1031 0.5881 0.0392
0.000 0.4714 0.00972 0.00192 -0.1026 0.5821 0.0444
0.250 0.4959 0.00926 0.00185 -0.1020 0.5765 0.1697
0.500 0.5212 0.00903 0.00187 -0.1015 0.5701 0.2528
0.750 0.5468 0.00895 0.00191 -0.1010 0.5644 0.3093
1.000 0.5732 0.00889 0.00196 -0.1006 0.5588 0.3487
1.250 0.5994 0.00887 0.00202 -0.1001 0.5526 0.3808
1.500 0.6251 0.00888 0.00207 -0.0996 0.5456 0.4105
1.750 0.6507 0.00885 0.00214 -0.0990 0.5365 0.4471
2.000 0.6758 0.00886 0.00221 -0.0984 0.5270 0.4806
2.250 0.7004 0.00887 0.00230 -0.0976 0.5163 0.5192
2.500 0.7256 0.00885 0.00239 -0.0969 0.5085 0.5639
2.750 0.7497 0.00887 0.00247 -0.0961 0.4989 0.6021
3.000 0.7729 0.00880 0.00257 -0.0950 0.4873 0.6621
3.500 0.8875 0.00862 0.00291 -0.1082 0.4545 1.0000
3.750 0.9116 0.00881 0.00303 -0.1074 0.4396 1.0000
4.000 0.9342 0.00907 0.00318 -0.1063 0.4179 1.0000
4.250 0.9563 0.00937 0.00336 -0.1051 0.3918 1.0000
4.500 0.9780 0.00969 0.00356 -0.1039 0.3693 1.0000
4.750 1.0001 0.01001 0.00378 -0.1028 0.3490 1.0000
5.000 1.0211 0.01038 0.00403 -0.1015 0.3267 1.0000
5.250 1.0421 0.01075 0.00430 -0.1001 0.3062 1.0000
5.500 1.0631 0.01112 0.00458 -0.0988 0.2853 1.0000
5.750 1.0819 0.01160 0.00492 -0.0972 0.2560 1.0000
6.000 1.0952 0.01242 0.00542 -0.0947 0.2000 1.0000
6.250 1.0978 0.01385 0.00635 -0.0905 0.1115 1.0000
6.500 1.1156 0.01435 0.00678 -0.0887 0.0955 1.0000
7.000 1.1491 0.01540 0.00767 -0.0848 0.0659 1.0000
7.250 1.1672 0.01581 0.00807 -0.0831 0.0616 1.0000
7.500 1.1839 0.01622 0.00848 -0.0812 0.0591 1.0000
7.750 1.1989 0.01665 0.00893 -0.0789 0.0568 1.0000
8.000 1.2130 0.01714 0.00942 -0.0765 0.0546 1.0000
8.250 1.2280 0.01760 0.00991 -0.0744 0.0532 1.0000
8.500 1.2437 0.01805 0.01040 -0.0724 0.0523 1.0000
8.750 1.2590 0.01854 0.01095 -0.0704 0.0514 1.0000
9.000 1.2737 0.01908 0.01153 -0.0685 0.0505 1.0000
9.250 1.2877 0.01967 0.01217 -0.0665 0.0493 1.0000
9.500 1.3007 0.02035 0.01287 -0.0645 0.0479 1.0000
9.750 1.3122 0.02114 0.01369 -0.0625 0.0465 1.0000
10.000 1.3205 0.02217 0.01475 -0.0602 0.0447 1.0000
10.250 1.3350 0.02286 0.01550 -0.0587 0.0440 1.0000
10.500 1.3486 0.02363 0.01634 -0.0572 0.0431 1.0000
10.750 1.3608 0.02454 0.01731 -0.0557 0.0422 1.0000
11.000 1.3732 0.02548 0.01830 -0.0544 0.0410 1.0000
11.250 1.3844 0.02652 0.01939 -0.0530 0.0399 1.0000
11.500 1.3944 0.02772 0.02062 -0.0517 0.0389 1.0000
11.750 1.4020 0.02914 0.02209 -0.0503 0.0380 1.0000
12.000 1.4108 0.03053 0.02354 -0.0490 0.0371 1.0000
12.250 1.4219 0.03176 0.02485 -0.0481 0.0363 1.0000
12.500 1.4315 0.03313 0.02630 -0.0471 0.0353 1.0000
12.750 1.4412 0.03454 0.02777 -0.0462 0.0342 1.0000
13.000 1.4499 0.03607 0.02935 -0.0453 0.0333 1.0000
13.250 1.4576 0.03771 0.03102 -0.0445 0.0321 1.0000
13.500 1.4628 0.03962 0.03299 -0.0437 0.0313 1.0000
13.750 1.4710 0.04127 0.03473 -0.0430 0.0302 1.0000
14.000 1.4784 0.04303 0.03656 -0.0423 0.0289 1.0000
14.250 1.4843 0.04496 0.03854 -0.0417 0.0278 1.0000
14.500 1.4891 0.04704 0.04066 -0.0411 0.0268 1.0000
14.750 1.4933 0.04923 0.04293 -0.0406 0.0259 1.0000
15.000 1.4976 0.05145 0.04524 -0.0402 0.0247 1.0000
15.250 1.5012 0.05377 0.04762 -0.0399 0.0235 1.0000
15.500 1.5038 0.05626 0.05015 -0.0396 0.0225 1.0000
15.750 1.5058 0.05887 0.05283 -0.0394 0.0214 1.0000
16.000 1.5074 0.06156 0.05560 -0.0392 0.0204 1.0000
16.250 1.5080 0.06441 0.05852 -0.0392 0.0195 1.0000
16.500 1.5077 0.06742 0.06160 -0.0393 0.0188 1.0000
16.750 1.5067 0.07057 0.06482 -0.0394 0.0182 1.0000
17.000 1.5062 0.07369 0.06803 -0.0396 0.0175 1.0000
17.250 1.5045 0.07703 0.07146 -0.0399 0.0169 1.0000
17.500 1.5021 0.08047 0.07498 -0.0403 0.0164 1.0000
17.750 1.4993 0.08403 0.07862 -0.0408 0.0159 1.0000
18.000 1.4954 0.08780 0.08246 -0.0414 0.0154 1.0000
18.250 1.4907 0.09173 0.08647 -0.0422 0.0150 1.0000
18.500 1.4872 0.09550 0.09034 -0.0430 0.0147 1.0000
18.750 1.4834 0.09937 0.09431 -0.0438 0.0143 1.0000
19.000 1.4794 0.10329 0.09833 -0.0448 0.0140 1.0000
19.250 1.4743 0.10746 0.10260 -0.0460 0.0137 1.0000
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