GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 500,000 Max Cl/Cd: 114.05 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe723-il-500000.txt Download as CSV file: xf-goe723-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2617 0.09750 0.09525 -0.0445 1.0000 0.0336
-10.250 -0.2566 0.09549 0.09326 -0.0435 1.0000 0.0338
-10.000 -0.2537 0.09340 0.09121 -0.0425 1.0000 0.0341
-9.750 -0.2448 0.09023 0.08805 -0.0438 0.9991 0.0346
-9.500 -0.2313 0.08620 0.08402 -0.0470 0.9970 0.0353
-9.250 -0.2201 0.08165 0.07946 -0.0506 0.9937 0.0363
-9.000 -0.2135 0.07640 0.07420 -0.0547 0.9889 0.0376
-8.750 -0.3243 0.08645 0.08418 -0.0434 0.9992 0.0354
-8.500 -0.3064 0.08181 0.07954 -0.0495 0.9955 0.0365
-8.250 -0.3242 0.06308 0.06081 -0.0743 0.9752 0.0396
-8.000 -0.3034 0.06112 0.05885 -0.0766 0.9641 0.0399
-7.750 -0.2799 0.05799 0.05571 -0.0816 0.9527 0.0404
-7.500 -0.2481 0.05367 0.05134 -0.0901 0.9428 0.0413
-7.250 -0.2287 0.03356 0.03002 -0.1200 0.9167 0.0471
-7.000 -0.1971 0.03151 0.02796 -0.1224 0.9018 0.0479
-6.750 -0.1719 0.02991 0.02622 -0.1235 0.8841 0.0490
-6.500 -0.1510 0.02838 0.02448 -0.1235 0.8665 0.0507
-6.250 -0.1391 0.02629 0.02167 -0.1225 0.8488 0.0555
-6.000 -0.1173 0.02455 0.01996 -0.1221 0.8352 0.0566
-5.750 -0.0953 0.02346 0.01879 -0.1216 0.8225 0.0581
-5.500 -0.0733 0.02257 0.01770 -0.1208 0.8105 0.0606
-5.250 -0.0574 0.01836 0.01244 -0.1180 0.7990 0.0473
-5.000 -0.0336 0.01627 0.00994 -0.1165 0.7888 0.0398
-4.750 -0.0083 0.01580 0.00930 -0.1158 0.7793 0.0395
-4.500 0.0170 0.01526 0.00867 -0.1152 0.7699 0.0393
-4.250 0.0423 0.01467 0.00795 -0.1145 0.7614 0.0392
-4.000 0.0674 0.01399 0.00720 -0.1139 0.7525 0.0392
-3.750 0.0922 0.01320 0.00631 -0.1132 0.7449 0.0394
-3.500 0.1165 0.01239 0.00549 -0.1124 0.7368 0.0399
-3.250 0.1413 0.01188 0.00493 -0.1117 0.7296 0.0404
-3.000 0.1664 0.01148 0.00451 -0.1110 0.7222 0.0408
-2.750 0.1917 0.01115 0.00414 -0.1104 0.7149 0.0413
-2.500 0.2173 0.01088 0.00383 -0.1098 0.7083 0.0419
-2.250 0.2430 0.01063 0.00355 -0.1092 0.7011 0.0427
-1.750 0.2950 0.01025 0.00309 -0.1081 0.6878 0.0444
-1.500 0.3213 0.01011 0.00289 -0.1076 0.6812 0.0454
-1.250 0.3473 0.00994 0.00269 -0.1070 0.6741 0.0473
-1.000 0.3732 0.00978 0.00249 -0.1064 0.6660 0.0501
-0.750 0.3996 0.00970 0.00235 -0.1059 0.6587 0.0534
-0.500 0.4257 0.00952 0.00223 -0.1053 0.6516 0.0674
-0.250 0.4482 0.00880 0.00218 -0.1046 0.6458 0.2860
0.000 0.4740 0.00865 0.00224 -0.1041 0.6394 0.3611
0.250 0.5000 0.00858 0.00227 -0.1036 0.6332 0.4046
0.500 0.5262 0.00857 0.00231 -0.1031 0.6273 0.4407
0.750 0.5523 0.00851 0.00235 -0.1026 0.6210 0.4714
1.000 0.5783 0.00848 0.00239 -0.1021 0.6151 0.5055
1.250 0.6042 0.00847 0.00245 -0.1015 0.6092 0.5410
1.500 0.6292 0.00837 0.00252 -0.1008 0.6027 0.5925
1.750 0.6523 0.00820 0.00257 -0.0997 0.5971 0.6723
2.000 0.7476 0.00766 0.00267 -0.1146 0.5878 1.0000
2.250 0.7728 0.00778 0.00269 -0.1139 0.5785 1.0000
2.500 0.7983 0.00784 0.00273 -0.1133 0.5685 1.0000
2.750 0.8237 0.00796 0.00279 -0.1126 0.5608 1.0000
3.000 0.8495 0.00804 0.00286 -0.1121 0.5526 1.0000
3.250 0.8745 0.00817 0.00294 -0.1114 0.5436 1.0000
3.500 0.8995 0.00828 0.00301 -0.1106 0.5331 1.0000
3.750 0.9245 0.00839 0.00311 -0.1099 0.5227 1.0000
4.000 0.9490 0.00855 0.00321 -0.1091 0.5134 1.0000
4.250 0.9741 0.00866 0.00333 -0.1085 0.5031 1.0000
4.500 0.9984 0.00881 0.00345 -0.1076 0.4914 1.0000
4.750 1.0221 0.00898 0.00358 -0.1067 0.4777 1.0000
5.000 1.0455 0.00917 0.00372 -0.1057 0.4628 1.0000
5.250 1.0686 0.00937 0.00388 -0.1047 0.4466 1.0000
5.500 1.0909 0.00961 0.00406 -0.1036 0.4264 1.0000
5.750 1.1120 0.00992 0.00428 -0.1022 0.4041 1.0000
6.000 1.1324 0.01027 0.00453 -0.1008 0.3791 1.0000
6.250 1.1510 0.01072 0.00484 -0.0990 0.3509 1.0000
6.500 1.1682 0.01125 0.00522 -0.0971 0.3190 1.0000
6.750 1.1832 0.01191 0.00567 -0.0947 0.2790 1.0000
7.000 1.1895 0.01306 0.00637 -0.0911 0.2010 1.0000
7.250 1.1841 0.01485 0.00757 -0.0856 0.1069 1.0000
7.500 1.1965 0.01559 0.00821 -0.0830 0.0869 1.0000
7.750 1.2092 0.01619 0.00875 -0.0803 0.0767 1.0000
8.000 1.2227 0.01669 0.00925 -0.0777 0.0720 1.0000
8.250 1.2344 0.01729 0.00984 -0.0750 0.0682 1.0000
8.500 1.2471 0.01788 0.01045 -0.0725 0.0654 1.0000
8.750 1.2608 0.01844 0.01106 -0.0702 0.0635 1.0000
9.000 1.2732 0.01909 0.01176 -0.0679 0.0614 1.0000
9.250 1.2835 0.01989 0.01257 -0.0654 0.0593 1.0000
9.500 1.2886 0.02101 0.01373 -0.0625 0.0570 1.0000
9.750 1.3005 0.02181 0.01460 -0.0605 0.0557 1.0000
10.000 1.3124 0.02265 0.01550 -0.0587 0.0545 1.0000
10.250 1.3233 0.02360 0.01652 -0.0569 0.0530 1.0000
10.500 1.3330 0.02467 0.01763 -0.0551 0.0515 1.0000
10.750 1.3402 0.02599 0.01899 -0.0533 0.0502 1.0000
11.000 1.3414 0.02783 0.02087 -0.0511 0.0486 1.0000
11.250 1.3463 0.02947 0.02259 -0.0494 0.0474 1.0000
11.500 1.3589 0.03056 0.02375 -0.0484 0.0463 1.0000
11.750 1.3688 0.03188 0.02515 -0.0473 0.0450 1.0000
12.000 1.3778 0.03332 0.02664 -0.0463 0.0437 1.0000
12.250 1.3859 0.03487 0.02823 -0.0453 0.0424 1.0000
12.500 1.3887 0.03692 0.03030 -0.0441 0.0412 1.0000
12.750 1.3901 0.03912 0.03256 -0.0428 0.0400 1.0000
13.000 1.4016 0.04046 0.03401 -0.0422 0.0387 1.0000
13.250 1.4098 0.04214 0.03576 -0.0415 0.0375 1.0000
13.500 1.4174 0.04389 0.03756 -0.0409 0.0363 1.0000
13.750 1.4231 0.04585 0.03955 -0.0403 0.0351 1.0000
14.000 1.4205 0.04857 0.04229 -0.0393 0.0340 1.0000
14.250 1.4285 0.05044 0.04427 -0.0389 0.0331 1.0000
14.500 1.4350 0.05245 0.04638 -0.0385 0.0319 1.0000
14.750 1.4410 0.05456 0.04856 -0.0383 0.0308 1.0000
15.000 1.4471 0.05674 0.05077 -0.0382 0.0297 1.0000
15.250 1.4469 0.05955 0.05360 -0.0379 0.0289 1.0000
15.500 1.4474 0.06229 0.05643 -0.0375 0.0281 1.0000
15.750 1.4515 0.06476 0.05902 -0.0375 0.0272 1.0000
16.000 1.4546 0.06737 0.06171 -0.0375 0.0265 1.0000
16.250 1.4568 0.07016 0.06457 -0.0376 0.0257 1.0000
16.500 1.4587 0.07302 0.06748 -0.0378 0.0251 1.0000
16.750 1.4584 0.07611 0.07061 -0.0381 0.0244 1.0000
17.000 1.4553 0.07943 0.07397 -0.0381 0.0238 1.0000
17.250 1.4564 0.08252 0.07720 -0.0385 0.0232 1.0000
17.500 1.4564 0.08571 0.08051 -0.0388 0.0227 1.0000
17.750 1.4561 0.08904 0.08392 -0.0394 0.0221 1.0000
18.000 1.4557 0.09236 0.08733 -0.0401 0.0216 1.0000
18.250 1.4543 0.09585 0.09089 -0.0408 0.0212 1.0000
18.500 1.4525 0.09939 0.09450 -0.0416 0.0208 1.0000
18.750 1.4499 0.10304 0.09818 -0.0424 0.0204 1.0000
19.000 1.4459 0.10667 0.10187 -0.0430 0.0199 1.0000
19.250 1.4430 0.11052 0.10585 -0.0441 0.0196 1.0000
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