GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 50,000 Max Cl/Cd: 43.75 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe164-il-50000-n5.txt Download as CSV file: xf-goe164-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 164 (MVA MK.10) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2778 0.10955 0.10356 -0.0238 1.0000 0.1006
-7.000 -0.2906 0.10924 0.10341 -0.0230 1.0000 0.1015
-6.750 -0.2992 0.10841 0.10272 -0.0234 1.0000 0.1019
-6.500 -0.3050 0.10717 0.10161 -0.0241 1.0000 0.1021
-6.250 -0.3043 0.10376 0.09830 -0.0218 1.0000 0.1026
-6.000 -0.3045 0.10090 0.09550 -0.0197 1.0000 0.1032
-5.500 -0.2461 0.08808 0.08250 -0.0411 0.9854 0.0622
-5.250 -0.2241 0.08389 0.07829 -0.0426 0.9785 0.0611
-5.000 -0.1968 0.07949 0.07383 -0.0477 0.9701 0.0599
-4.750 -0.1663 0.07491 0.06919 -0.0540 0.9614 0.0579
-4.500 -0.1275 0.06960 0.06379 -0.0629 0.9539 0.0557
-4.250 -0.0904 0.06433 0.05840 -0.0714 0.9440 0.0544
-4.000 -0.0453 0.05890 0.05281 -0.0813 0.9362 0.0561
-3.750 0.0088 0.05235 0.04598 -0.0934 0.9289 0.0585
-3.250 0.1361 0.03693 0.02924 -0.1196 0.9193 0.0656
-3.000 0.1903 0.03253 0.02398 -0.1269 0.9143 0.0732
-2.750 0.2300 0.03105 0.02220 -0.1299 0.9063 0.0854
-2.500 0.2712 0.02968 0.02050 -0.1327 0.8987 0.0996
-2.250 0.3062 0.02920 0.01986 -0.1341 0.8886 0.1189
-2.000 0.3458 0.02871 0.01917 -0.1359 0.8797 0.1491
-1.750 0.3856 0.02825 0.01834 -0.1378 0.8696 0.1900
-1.500 0.4205 0.02803 0.01802 -0.1386 0.8570 0.2224
-1.250 0.4563 0.02771 0.01763 -0.1394 0.8441 0.2549
-1.000 0.4949 0.02693 0.01658 -0.1408 0.8316 0.2696
-0.750 0.5341 0.02623 0.01548 -0.1422 0.8196 0.2792
-0.500 0.5736 0.02559 0.01462 -0.1437 0.8099 0.2882
-0.250 0.6068 0.02525 0.01400 -0.1442 0.7971 0.2949
0.000 0.6394 0.02494 0.01356 -0.1447 0.7846 0.3018
0.250 0.6725 0.02469 0.01312 -0.1451 0.7722 0.3115
0.500 0.7050 0.02444 0.01276 -0.1455 0.7594 0.3207
0.750 0.7371 0.02422 0.01242 -0.1458 0.7465 0.3295
1.000 0.7684 0.02405 0.01216 -0.1459 0.7332 0.3412
1.250 0.7964 0.02399 0.01206 -0.1455 0.7186 0.3556
1.500 0.8239 0.02393 0.01201 -0.1451 0.7038 0.3718
1.750 0.8510 0.02386 0.01197 -0.1446 0.6889 0.3912
2.000 0.8776 0.02375 0.01198 -0.1441 0.6740 0.4216
2.250 0.9030 0.02341 0.01208 -0.1435 0.6590 0.4972
2.500 0.9253 0.02296 0.01201 -0.1418 0.6434 1.0000
2.750 0.9517 0.02322 0.01206 -0.1411 0.6275 1.0000
3.000 0.9777 0.02350 0.01219 -0.1404 0.6116 1.0000
3.250 1.0025 0.02383 0.01237 -0.1395 0.5952 1.0000
3.500 1.0269 0.02417 0.01261 -0.1386 0.5785 1.0000
3.750 1.0512 0.02454 0.01289 -0.1376 0.5620 1.0000
4.000 1.0753 0.02492 0.01319 -0.1367 0.5460 1.0000
4.250 1.0996 0.02534 0.01353 -0.1359 0.5310 1.0000
4.500 1.1237 0.02579 0.01394 -0.1351 0.5167 1.0000
4.750 1.1478 0.02626 0.01435 -0.1342 0.5031 1.0000
5.000 1.1712 0.02677 0.01484 -0.1333 0.4899 1.0000
5.250 1.1933 0.02733 0.01543 -0.1323 0.4766 1.0000
5.500 1.2152 0.02792 0.01608 -0.1313 0.4639 1.0000
5.750 1.2373 0.02851 0.01671 -0.1303 0.4523 1.0000
6.000 1.2607 0.02908 0.01729 -0.1295 0.4423 1.0000
6.250 1.2820 0.02974 0.01809 -0.1284 0.4316 1.0000
6.500 1.3026 0.03044 0.01888 -0.1273 0.4210 1.0000
6.750 1.3242 0.03107 0.01956 -0.1262 0.4110 1.0000
7.000 1.3448 0.03174 0.02032 -0.1250 0.4008 1.0000
7.250 1.3635 0.03253 0.02125 -0.1236 0.3904 1.0000
7.500 1.3840 0.03324 0.02208 -0.1225 0.3809 1.0000
7.750 1.4032 0.03402 0.02299 -0.1211 0.3712 1.0000
8.000 1.4208 0.03492 0.02407 -0.1197 0.3617 1.0000
8.250 1.4427 0.03564 0.02485 -0.1187 0.3535 1.0000
8.500 1.4573 0.03677 0.02626 -0.1169 0.3446 1.0000
9.000 1.4929 0.03888 0.02886 -0.1142 0.3298 1.0000
9.250 1.5141 0.03985 0.03000 -0.1133 0.3234 1.0000
9.500 1.5268 0.04124 0.03171 -0.1114 0.3166 1.0000
9.750 1.5423 0.04239 0.03312 -0.1098 0.3095 1.0000
10.000 1.5490 0.04364 0.03462 -0.1071 0.3003 1.0000
10.250 1.5513 0.04446 0.03557 -0.1035 0.2884 1.0000
10.500 1.5462 0.04543 0.03664 -0.0992 0.2759 1.0000
10.750 1.5347 0.04729 0.03885 -0.0951 0.2646 1.0000
11.000 1.5252 0.04933 0.04112 -0.0916 0.2535 1.0000
11.250 1.5161 0.05162 0.04361 -0.0888 0.2425 1.0000
11.500 1.5057 0.05432 0.04650 -0.0866 0.2307 1.0000
11.750 1.4944 0.05749 0.04985 -0.0851 0.2180 1.0000
12.000 1.4837 0.06099 0.05350 -0.0841 0.2051 1.0000
12.250 1.4724 0.06480 0.05740 -0.0835 0.1916 1.0000
12.500 1.4594 0.06907 0.06168 -0.0833 0.1774 1.0000
12.750 1.4457 0.07373 0.06635 -0.0835 0.1645 1.0000
13.000 1.4290 0.07938 0.07219 -0.0843 0.1516 1.0000
13.250 1.4102 0.08593 0.07905 -0.0860 0.1381 1.0000
13.500 1.3894 0.09330 0.08681 -0.0883 0.1246 1.0000
13.750 1.3720 0.09911 0.09224 -0.0898 0.0938 1.0000
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Polar data table (+)
Polar graphs
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