GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 200,000 Max Cl/Cd: 79.45 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe184-il-200000-n5.txt Download as CSV file: xf-goe184-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3081 0.08972 0.08638 -0.0287 1.0000 0.0225
-7.750 -0.3089 0.08711 0.08383 -0.0287 1.0000 0.0223
-7.500 -0.3138 0.08475 0.08155 -0.0281 0.9998 0.0222
-7.250 -0.2918 0.07910 0.07588 -0.0366 0.9881 0.0224
-7.000 -0.2680 0.07462 0.07139 -0.0437 0.9767 0.0239
-6.750 -0.2437 0.07164 0.06839 -0.0482 0.9660 0.0256
-6.500 -0.2180 0.06622 0.06292 -0.0565 0.9531 0.0259
-6.250 -0.1904 0.06044 0.05706 -0.0650 0.9396 0.0261
-6.000 -0.1599 0.05404 0.05052 -0.0741 0.9257 0.0273
-5.750 -0.1187 0.03970 0.03574 -0.0909 0.9115 0.0289
-5.500 -0.0890 0.03475 0.03051 -0.0957 0.8990 0.0299
-5.250 -0.0617 0.03375 0.02940 -0.0967 0.8863 0.0313
-5.000 -0.0267 0.02016 0.01418 -0.1049 0.8752 0.0334
-4.750 0.0016 0.01828 0.01178 -0.1054 0.8628 0.0348
-4.500 0.0296 0.01705 0.01015 -0.1054 0.8501 0.0358
-4.250 0.0570 0.01585 0.00868 -0.1054 0.8369 0.0366
-4.000 0.0843 0.01507 0.00769 -0.1051 0.8231 0.0374
-3.750 0.1116 0.01448 0.00692 -0.1048 0.8086 0.0382
-3.500 0.1387 0.01401 0.00629 -0.1044 0.7932 0.0396
-3.250 0.1659 0.01361 0.00570 -0.1041 0.7773 0.0412
-3.000 0.1931 0.01325 0.00517 -0.1037 0.7614 0.0423
-2.750 0.2205 0.01295 0.00472 -0.1033 0.7460 0.0432
-2.500 0.2479 0.01272 0.00439 -0.1030 0.7319 0.0449
-2.250 0.2756 0.01255 0.00418 -0.1028 0.7186 0.0472
-1.750 0.3309 0.01241 0.00397 -0.1023 0.6918 0.0591
-1.500 0.3586 0.01238 0.00381 -0.1020 0.6782 0.0695
-1.250 0.3863 0.01240 0.00371 -0.1017 0.6640 0.0773
-1.000 0.4138 0.01233 0.00358 -0.1015 0.6488 0.0832
-0.750 0.4412 0.01230 0.00346 -0.1013 0.6325 0.0869
-0.500 0.4686 0.01230 0.00335 -0.1010 0.6157 0.0899
-0.250 0.4958 0.01227 0.00325 -0.1008 0.5994 0.0938
0.000 0.5230 0.01228 0.00318 -0.1006 0.5846 0.0975
0.250 0.5502 0.01231 0.00313 -0.1004 0.5717 0.0999
0.500 0.5774 0.01237 0.00310 -0.1001 0.5601 0.1040
0.750 0.6045 0.01241 0.00312 -0.1000 0.5488 0.1109
1.000 0.6317 0.01248 0.00315 -0.0998 0.5377 0.1183
1.250 0.6589 0.01254 0.00319 -0.0996 0.5269 0.1236
1.750 0.7132 0.01268 0.00331 -0.0993 0.5060 0.1419
2.000 0.7403 0.01272 0.00340 -0.0991 0.4969 0.1698
2.250 0.7673 0.01264 0.00356 -0.0990 0.4874 0.2643
2.500 0.7931 0.01224 0.00372 -0.0989 0.4780 0.5050
3.000 0.8428 0.01169 0.00390 -0.0971 0.4592 1.0000
3.250 0.8697 0.01189 0.00403 -0.0969 0.4500 1.0000
3.500 0.8965 0.01208 0.00419 -0.0967 0.4399 1.0000
3.750 0.9233 0.01227 0.00435 -0.0965 0.4289 1.0000
4.000 0.9497 0.01248 0.00451 -0.0962 0.4177 1.0000
4.250 0.9760 0.01271 0.00470 -0.0959 0.4065 1.0000
4.500 1.0023 0.01293 0.00490 -0.0957 0.3955 1.0000
4.750 1.0285 0.01317 0.00512 -0.0954 0.3858 1.0000
5.000 1.0543 0.01344 0.00537 -0.0951 0.3773 1.0000
5.250 1.0804 0.01369 0.00564 -0.0948 0.3689 1.0000
5.500 1.1060 0.01399 0.00592 -0.0944 0.3611 1.0000
5.750 1.1317 0.01426 0.00624 -0.0941 0.3522 1.0000
6.000 1.1569 0.01458 0.00656 -0.0937 0.3431 1.0000
6.250 1.1822 0.01488 0.00690 -0.0933 0.3351 1.0000
6.500 1.2070 0.01521 0.00726 -0.0929 0.3254 1.0000
6.750 1.2310 0.01560 0.00764 -0.0924 0.3111 1.0000
7.000 1.2548 0.01598 0.00804 -0.0918 0.2954 1.0000
7.250 1.2787 0.01636 0.00845 -0.0913 0.2823 1.0000
7.500 1.3021 0.01677 0.00888 -0.0907 0.2613 1.0000
7.750 1.3227 0.01740 0.00939 -0.0898 0.2204 1.0000
8.000 1.3388 0.01849 0.01017 -0.0885 0.1782 1.0000
8.250 1.3565 0.01943 0.01103 -0.0873 0.1598 1.0000
8.500 1.3751 0.02025 0.01184 -0.0861 0.1443 1.0000
8.750 1.3934 0.02106 0.01264 -0.0850 0.1205 1.0000
9.000 1.4051 0.02241 0.01374 -0.0831 0.0847 1.0000
9.250 1.4146 0.02385 0.01504 -0.0810 0.0474 1.0000
9.500 1.4202 0.02552 0.01656 -0.0783 0.0343 1.0000
9.750 1.4260 0.02693 0.01803 -0.0755 0.0296 1.0000
10.000 1.4338 0.02815 0.01938 -0.0731 0.0269 1.0000
10.250 1.4408 0.02948 0.02087 -0.0708 0.0248 1.0000
10.500 1.4449 0.03110 0.02264 -0.0686 0.0231 1.0000
10.750 1.4448 0.03317 0.02485 -0.0664 0.0216 1.0000
11.000 1.4463 0.03525 0.02707 -0.0646 0.0204 1.0000
11.250 1.4500 0.03726 0.02924 -0.0634 0.0194 1.0000
11.500 1.4516 0.03959 0.03171 -0.0623 0.0183 1.0000
11.750 1.4513 0.04227 0.03453 -0.0615 0.0176 1.0000
12.000 1.4495 0.04524 0.03764 -0.0609 0.0170 1.0000
12.250 1.4461 0.04850 0.04104 -0.0606 0.0164 1.0000
12.500 1.4407 0.05214 0.04479 -0.0605 0.0160 1.0000
12.750 1.4328 0.05618 0.04896 -0.0607 0.0156 1.0000
13.000 1.4223 0.06066 0.05354 -0.0609 0.0152 1.0000
13.250 1.4195 0.06424 0.05727 -0.0612 0.0149 1.0000
13.500 1.4160 0.06795 0.06113 -0.0616 0.0144 1.0000
13.750 1.4122 0.07179 0.06510 -0.0620 0.0140 1.0000
14.000 1.4080 0.07572 0.06915 -0.0626 0.0135 1.0000
14.250 1.4039 0.07971 0.07326 -0.0632 0.0131 1.0000
14.500 1.3998 0.08375 0.07741 -0.0640 0.0128 1.0000
14.750 1.3956 0.08781 0.08158 -0.0647 0.0125 1.0000
15.000 1.3917 0.09187 0.08573 -0.0655 0.0122 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 184 (MVA H.29) AIRFOIL (goe184-il)