GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 500,000 Max Cl/Cd: 93.24 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe534-il-500000.txt Download as CSV file: xf-goe534-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7196 0.06884 0.06558 -0.0608 1.0000 0.0356
-13.750 -0.7762 0.05734 0.05387 -0.0700 1.0000 0.0354
-13.500 -0.8099 0.04999 0.04637 -0.0757 1.0000 0.0354
-13.250 -0.8407 0.04419 0.04047 -0.0794 1.0000 0.0353
-13.000 -0.8652 0.03862 0.03478 -0.0838 1.0000 0.0353
-12.750 -0.8671 0.03344 0.02938 -0.0900 1.0000 0.0355
-12.500 -0.8577 0.03024 0.02596 -0.0930 1.0000 0.0357
-12.250 -0.8461 0.02832 0.02386 -0.0934 1.0000 0.0359
-12.000 -0.8367 0.02629 0.02173 -0.0927 1.0000 0.0363
-11.750 -0.8232 0.02489 0.02029 -0.0917 1.0000 0.0368
-11.500 -0.8076 0.02378 0.01916 -0.0907 1.0000 0.0373
-11.250 -0.7915 0.02278 0.01811 -0.0895 1.0000 0.0378
-11.000 -0.7754 0.02186 0.01713 -0.0882 1.0000 0.0382
-10.750 -0.7394 0.02077 0.01593 -0.0906 0.9972 0.0389
-10.500 -0.7006 0.01973 0.01477 -0.0934 0.9934 0.0395
-10.250 -0.6641 0.01881 0.01372 -0.0954 0.9887 0.0401
-10.000 -0.6278 0.01771 0.01258 -0.0976 0.9836 0.0409
-9.750 -0.5907 0.01683 0.01168 -0.0998 0.9787 0.0418
-9.500 -0.5562 0.01613 0.01095 -0.1011 0.9710 0.0429
-9.250 -0.5191 0.01545 0.01020 -0.1029 0.9645 0.0440
-9.000 -0.4831 0.01483 0.00949 -0.1044 0.9543 0.0450
-8.750 -0.4469 0.01411 0.00877 -0.1060 0.9421 0.0465
-8.500 -0.4083 0.01359 0.00821 -0.1079 0.9270 0.0482
-8.250 -0.3716 0.01311 0.00764 -0.1093 0.9067 0.0503
-8.000 -0.3393 0.01282 0.00729 -0.1098 0.8833 0.0528
-7.750 -0.3106 0.01263 0.00699 -0.1094 0.8606 0.0562
-7.500 -0.2827 0.01262 0.00689 -0.1089 0.8406 0.0601
-7.250 -0.2549 0.01264 0.00684 -0.1083 0.8235 0.0644
-7.000 -0.2270 0.01269 0.00677 -0.1077 0.8088 0.0692
-6.750 -0.1993 0.01277 0.00680 -0.1071 0.7953 0.0727
-6.500 -0.1713 0.01291 0.00674 -0.1066 0.7820 0.0761
-6.250 -0.1448 0.01268 0.00653 -0.1060 0.7699 0.0790
-6.000 -0.1174 0.01269 0.00645 -0.1054 0.7584 0.0818
-5.750 -0.0897 0.01274 0.00637 -0.1048 0.7460 0.0841
-5.500 -0.0637 0.01233 0.00594 -0.1042 0.7343 0.0866
-5.250 -0.0368 0.01222 0.00578 -0.1036 0.7222 0.0889
-5.000 -0.0094 0.01210 0.00561 -0.1030 0.7097 0.0910
-4.750 0.0177 0.01201 0.00542 -0.1024 0.6967 0.0926
-4.500 0.0448 0.01189 0.00521 -0.1018 0.6823 0.0942
-4.250 0.0711 0.01150 0.00480 -0.1011 0.6671 0.0963
-4.000 0.0979 0.01134 0.00459 -0.1005 0.6504 0.0980
-3.750 0.1247 0.01123 0.00441 -0.0999 0.6319 0.1000
-3.500 0.1515 0.01114 0.00422 -0.0992 0.6117 0.1016
-3.250 0.1781 0.01109 0.00405 -0.0985 0.5906 0.1030
-3.000 0.2049 0.01110 0.00393 -0.0978 0.5707 0.1042
-2.750 0.2310 0.01089 0.00365 -0.0971 0.5539 0.1064
-2.500 0.2576 0.01080 0.00350 -0.0965 0.5398 0.1087
-2.250 0.2846 0.01077 0.00340 -0.0959 0.5271 0.1106
-2.000 0.3120 0.01071 0.00330 -0.0954 0.5164 0.1122
-1.500 0.3668 0.01066 0.00313 -0.0944 0.4967 0.1153
-1.250 0.3938 0.01063 0.00304 -0.0938 0.4873 0.1179
-1.000 0.4215 0.01055 0.00297 -0.0934 0.4792 0.1218
-0.750 0.4489 0.01054 0.00293 -0.0929 0.4709 0.1269
-0.500 0.4762 0.01047 0.00289 -0.0924 0.4632 0.1381
-0.250 0.5033 0.01028 0.00287 -0.0920 0.4549 0.1862
0.000 0.5298 0.01021 0.00292 -0.0914 0.4468 0.2465
0.250 0.5575 0.01017 0.00297 -0.0910 0.4395 0.2801
0.500 0.5846 0.01021 0.00304 -0.0905 0.4318 0.3034
0.750 0.6120 0.01026 0.00311 -0.0901 0.4246 0.3226
1.000 0.6394 0.01032 0.00317 -0.0896 0.4164 0.3397
1.250 0.6661 0.01042 0.00326 -0.0890 0.4084 0.3565
1.500 0.6937 0.01045 0.00334 -0.0886 0.4007 0.3740
1.750 0.7203 0.01056 0.00344 -0.0880 0.3927 0.3895
2.000 0.7476 0.01063 0.00353 -0.0876 0.3848 0.4046
2.250 0.7743 0.01075 0.00362 -0.0870 0.3759 0.4185
2.500 0.8010 0.01084 0.00373 -0.0865 0.3678 0.4321
2.750 0.8275 0.01095 0.00383 -0.0859 0.3590 0.4448
3.000 0.8540 0.01108 0.00395 -0.0854 0.3504 0.4595
3.250 0.8801 0.01120 0.00408 -0.0848 0.3409 0.4734
3.500 0.9061 0.01133 0.00421 -0.0842 0.3319 0.4871
3.750 0.9318 0.01148 0.00435 -0.0835 0.3224 0.5021
4.000 0.9575 0.01161 0.00450 -0.0828 0.3133 0.5202
4.250 0.9823 0.01177 0.00467 -0.0821 0.3040 0.5398
4.500 1.0076 0.01188 0.00484 -0.0814 0.2955 0.5639
4.750 1.0313 0.01201 0.00503 -0.0805 0.2870 0.6027
5.000 1.0783 0.01157 0.00529 -0.0844 0.2775 1.0000
5.250 1.1027 0.01186 0.00550 -0.0837 0.2701 1.0000
5.500 1.1277 0.01210 0.00571 -0.0829 0.2639 1.0000
5.750 1.1524 0.01236 0.00593 -0.0822 0.2577 1.0000
6.000 1.1754 0.01273 0.00621 -0.0812 0.2512 1.0000
6.250 1.2007 0.01293 0.00642 -0.0806 0.2464 1.0000
6.500 1.2247 0.01321 0.00667 -0.0798 0.2412 1.0000
6.750 1.2471 0.01359 0.00699 -0.0787 0.2359 1.0000
7.000 1.2713 0.01383 0.00725 -0.0779 0.2316 1.0000
7.250 1.2950 0.01410 0.00751 -0.0771 0.2271 1.0000
7.500 1.3171 0.01445 0.00783 -0.0760 0.2226 1.0000
7.750 1.3386 0.01484 0.00819 -0.0749 0.2181 1.0000
8.000 1.3622 0.01508 0.00846 -0.0740 0.2143 1.0000
8.250 1.3842 0.01540 0.00878 -0.0730 0.2100 1.0000
8.500 1.4040 0.01583 0.00916 -0.0716 0.2055 1.0000
8.750 1.4249 0.01617 0.00953 -0.0704 0.2016 1.0000
9.000 1.4467 0.01645 0.00984 -0.0694 0.1976 1.0000
9.250 1.4661 0.01683 0.01021 -0.0680 0.1935 1.0000
9.500 1.4821 0.01735 0.01068 -0.0661 0.1892 1.0000
9.750 1.5006 0.01766 0.01105 -0.0645 0.1861 1.0000
10.000 1.5182 0.01799 0.01143 -0.0628 0.1824 1.0000
10.250 1.5332 0.01844 0.01187 -0.0608 0.1787 1.0000
10.500 1.5448 0.01906 0.01246 -0.0584 0.1748 1.0000
10.750 1.5615 0.01947 0.01293 -0.0568 0.1718 1.0000
11.000 1.5774 0.01993 0.01344 -0.0551 0.1683 1.0000
11.250 1.5905 0.02054 0.01406 -0.0532 0.1647 1.0000
11.500 1.5998 0.02138 0.01488 -0.0510 0.1611 1.0000
11.750 1.6144 0.02199 0.01556 -0.0495 0.1580 1.0000
12.000 1.6278 0.02269 0.01631 -0.0480 0.1545 1.0000
12.250 1.6381 0.02361 0.01724 -0.0464 0.1511 1.0000
12.500 1.6439 0.02488 0.01850 -0.0446 0.1476 1.0000
12.750 1.6569 0.02576 0.01947 -0.0435 0.1449 1.0000
13.000 1.6675 0.02685 0.02062 -0.0423 0.1417 1.0000
13.250 1.6749 0.02823 0.02203 -0.0412 0.1388 1.0000
13.500 1.6781 0.03003 0.02383 -0.0400 0.1357 1.0000
13.750 1.6866 0.03146 0.02535 -0.0392 0.1332 1.0000
14.000 1.6946 0.03300 0.02696 -0.0384 0.1305 1.0000
14.250 1.6993 0.03488 0.02889 -0.0378 0.1279 1.0000
14.500 1.7000 0.03718 0.03121 -0.0371 0.1253 1.0000
14.750 1.6991 0.03968 0.03376 -0.0366 0.1228 1.0000
15.000 1.7046 0.04165 0.03583 -0.0363 0.1207 1.0000
15.250 1.7064 0.04402 0.03828 -0.0360 0.1184 1.0000
15.500 1.7051 0.04679 0.04110 -0.0359 0.1163 1.0000
15.750 1.6989 0.05017 0.04451 -0.0360 0.1138 1.0000
16.000 1.6944 0.05343 0.04784 -0.0362 0.1116 1.0000
16.250 1.6949 0.05627 0.05078 -0.0365 0.1098 1.0000
16.500 1.6927 0.05950 0.05410 -0.0370 0.1075 1.0000
16.750 1.6867 0.06321 0.05787 -0.0376 0.1054 1.0000
17.000 1.6783 0.06725 0.06194 -0.0384 0.1036 1.0000
17.250 1.6709 0.07119 0.06593 -0.0391 0.1015 1.0000
17.500 1.6676 0.07477 0.06962 -0.0400 0.0999 1.0000
17.750 1.6625 0.07862 0.07357 -0.0409 0.0981 1.0000
18.000 1.6563 0.08264 0.07766 -0.0420 0.0965 1.0000
18.250 1.6489 0.08683 0.08189 -0.0432 0.0950 1.0000
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