GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 500,000 Max Cl/Cd: 107.45 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe184-il-500000.txt Download as CSV file: xf-goe184-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 184 (MVA H.29) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3191 0.09284 0.09067 -0.0231 1.0000 0.0230
-8.000 -0.3133 0.08994 0.08780 -0.0244 1.0000 0.0237
-7.750 -0.3098 0.08703 0.08492 -0.0257 1.0000 0.0245
-7.500 -0.2305 0.06529 0.06337 -0.0410 0.9874 0.0267
-7.250 -0.2127 0.06190 0.05997 -0.0428 0.9803 0.0272
-7.000 -0.1944 0.05861 0.05667 -0.0455 0.9706 0.0280
-6.750 -0.1789 0.05503 0.05308 -0.0491 0.9560 0.0293
-6.500 -0.1671 0.05044 0.04844 -0.0543 0.9368 0.0313
-6.250 -0.1466 0.04309 0.04097 -0.0665 0.9183 0.0327
-6.000 -0.1398 0.03826 0.03609 -0.0677 0.8998 0.0338
-5.750 -0.1238 0.03631 0.03405 -0.0678 0.8813 0.0347
-5.500 -0.1047 0.03353 0.03117 -0.0699 0.8644 0.0364
-5.250 -0.0718 0.02074 0.01678 -0.0998 0.9021 0.0333
-5.000 -0.0461 0.01808 0.01361 -0.1001 0.8852 0.0331
-4.750 -0.0205 0.01521 0.01019 -0.1003 0.8688 0.0336
-4.500 0.0057 0.01378 0.00846 -0.1001 0.8522 0.0345
-4.250 0.0326 0.01282 0.00722 -0.0998 0.8358 0.0350
-4.000 0.0597 0.01207 0.00625 -0.0995 0.8198 0.0356
-3.750 0.0871 0.01147 0.00546 -0.0992 0.8046 0.0363
-3.500 0.1147 0.01100 0.00484 -0.0989 0.7904 0.0374
-3.250 0.1426 0.01057 0.00426 -0.0987 0.7777 0.0382
-3.000 0.1705 0.01019 0.00377 -0.0985 0.7653 0.0388
-2.750 0.1984 0.00989 0.00335 -0.0983 0.7528 0.0394
-2.500 0.2263 0.00966 0.00299 -0.0981 0.7404 0.0400
-2.250 0.2544 0.00943 0.00268 -0.0979 0.7278 0.0409
-2.000 0.2827 0.00923 0.00243 -0.0978 0.7151 0.0434
-1.750 0.3108 0.00910 0.00225 -0.0976 0.7019 0.0460
-1.500 0.3389 0.00902 0.00219 -0.0975 0.6877 0.0521
-1.250 0.3670 0.00905 0.00220 -0.0973 0.6722 0.0657
-1.000 0.3950 0.00909 0.00218 -0.0971 0.6547 0.0726
-0.750 0.4228 0.00920 0.00219 -0.0969 0.6355 0.0788
-0.500 0.4505 0.00921 0.00213 -0.0967 0.6147 0.0847
-0.250 0.4780 0.00929 0.00211 -0.0966 0.5938 0.0897
0.000 0.5055 0.00940 0.00211 -0.0964 0.5761 0.0929
0.250 0.5331 0.00942 0.00206 -0.0963 0.5615 0.0960
0.500 0.5609 0.00944 0.00204 -0.0962 0.5493 0.0994
0.750 0.5886 0.00950 0.00206 -0.0961 0.5386 0.1029
1.000 0.6163 0.00957 0.00207 -0.0960 0.5289 0.1051
1.250 0.6442 0.00962 0.00211 -0.0959 0.5198 0.1077
1.500 0.6719 0.00966 0.00213 -0.0959 0.5108 0.1124
1.750 0.6997 0.00970 0.00218 -0.0958 0.4999 0.1179
2.000 0.7275 0.00975 0.00222 -0.0957 0.4890 0.1234
2.250 0.7552 0.00979 0.00229 -0.0956 0.4786 0.1399
2.500 0.7831 0.00957 0.00244 -0.0958 0.4682 0.2976
2.750 0.8047 0.00822 0.00258 -0.0946 0.4587 1.0000
3.000 0.8322 0.00837 0.00266 -0.0945 0.4485 1.0000
3.250 0.8598 0.00851 0.00274 -0.0943 0.4372 1.0000
3.500 0.8873 0.00865 0.00283 -0.0942 0.4253 1.0000
3.750 0.9146 0.00882 0.00294 -0.0941 0.4124 1.0000
4.000 0.9417 0.00900 0.00307 -0.0940 0.4002 1.0000
4.250 0.9687 0.00921 0.00321 -0.0938 0.3893 1.0000
4.500 0.9958 0.00939 0.00337 -0.0937 0.3797 1.0000
4.750 1.0227 0.00959 0.00355 -0.0935 0.3715 1.0000
5.250 1.0758 0.01005 0.00393 -0.0931 0.3503 1.0000
5.500 1.1024 0.01028 0.00414 -0.0929 0.3416 1.0000
5.750 1.1285 0.01054 0.00438 -0.0927 0.3320 1.0000
6.000 1.1551 0.01075 0.00459 -0.0925 0.3223 1.0000
6.250 1.1812 0.01100 0.00484 -0.0923 0.3118 1.0000
6.500 1.2069 0.01128 0.00510 -0.0920 0.2993 1.0000
6.750 1.2327 0.01155 0.00535 -0.0917 0.2838 1.0000
7.000 1.2579 0.01188 0.00562 -0.0914 0.2606 1.0000
7.250 1.2803 0.01253 0.00602 -0.0908 0.2099 1.0000
7.500 1.2997 0.01354 0.00674 -0.0898 0.1669 1.0000
7.750 1.3214 0.01424 0.00735 -0.0890 0.1476 1.0000
8.000 1.3431 0.01492 0.00792 -0.0883 0.1197 1.0000
8.250 1.3581 0.01633 0.00894 -0.0867 0.0654 1.0000
8.500 1.3716 0.01782 0.01019 -0.0849 0.0320 1.0000
8.750 1.3916 0.01856 0.01102 -0.0838 0.0289 1.0000
9.000 1.4088 0.01951 0.01206 -0.0823 0.0262 1.0000
9.250 1.4235 0.02064 0.01328 -0.0806 0.0240 1.0000
9.500 1.4413 0.02140 0.01412 -0.0792 0.0227 1.0000
9.750 1.4565 0.02230 0.01511 -0.0776 0.0213 1.0000
10.000 1.4681 0.02341 0.01629 -0.0755 0.0202 1.0000
10.250 1.4694 0.02493 0.01790 -0.0720 0.0193 1.0000
10.500 1.4674 0.02674 0.01983 -0.0685 0.0186 1.0000
10.750 1.4765 0.02790 0.02109 -0.0666 0.0182 1.0000
11.000 1.4831 0.02932 0.02261 -0.0647 0.0176 1.0000
11.250 1.4886 0.03094 0.02433 -0.0630 0.0169 1.0000
11.500 1.4938 0.03271 0.02618 -0.0616 0.0163 1.0000
11.750 1.4976 0.03471 0.02827 -0.0604 0.0157 1.0000
12.000 1.4991 0.03710 0.03073 -0.0594 0.0153 1.0000
12.250 1.4963 0.04003 0.03374 -0.0585 0.0149 1.0000
12.500 1.4887 0.04358 0.03739 -0.0575 0.0146 1.0000
12.750 1.4812 0.04712 0.04103 -0.0564 0.0143 1.0000
13.000 1.4844 0.04968 0.04371 -0.0561 0.0141 1.0000
13.250 1.4857 0.05245 0.04659 -0.0558 0.0138 1.0000
13.500 1.4859 0.05539 0.04964 -0.0555 0.0136 1.0000
13.750 1.4855 0.05843 0.05279 -0.0553 0.0133 1.0000
14.000 1.4846 0.06153 0.05600 -0.0551 0.0131 1.0000
14.250 1.4836 0.06471 0.05928 -0.0550 0.0128 1.0000
14.500 1.4827 0.06797 0.06264 -0.0551 0.0125 1.0000
14.750 1.4814 0.07136 0.06612 -0.0554 0.0123 1.0000
15.000 1.4796 0.07490 0.06976 -0.0559 0.0120 1.0000
15.250 1.4776 0.07855 0.07349 -0.0566 0.0118 1.0000
15.500 1.4753 0.08223 0.07725 -0.0572 0.0116 1.0000
15.750 1.4727 0.08584 0.08093 -0.0577 0.0113 1.0000
16.000 1.4696 0.08920 0.08436 -0.0573 0.0111 1.0000
16.250 1.4637 0.09299 0.08829 -0.0565 0.0108 1.0000
16.500 1.4573 0.09770 0.09315 -0.0581 0.0108 1.0000
16.750 1.4500 0.10264 0.09825 -0.0599 0.0107 1.0000
17.000 1.4423 0.10770 0.10347 -0.0618 0.0106 1.0000
17.250 1.4337 0.11305 0.10898 -0.0640 0.0105 1.0000
17.500 1.4244 0.11861 0.11470 -0.0664 0.0105 1.0000
17.750 1.4142 0.12451 0.12077 -0.0692 0.0104 1.0000
18.000 1.4030 0.13074 0.12716 -0.0723 0.0104 1.0000
18.250 1.3909 0.13736 0.13395 -0.0758 0.0103 1.0000
18.500 1.3788 0.14423 0.14099 -0.0798 0.0103 1.0000
18.750 1.3656 0.15158 0.14850 -0.0842 0.0103 1.0000
19.000 1.3517 0.15934 0.15641 -0.0891 0.0103 1.0000
19.250 1.3371 0.16759 0.16482 -0.0945 0.0103 1.0000
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