GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 500,000 Max Cl/Cd: 104.57 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe164-il-500000.txt Download as CSV file: xf-goe164-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3033 0.11238 0.11020 -0.0248 1.0000 0.0175
-9.000 -0.3054 0.10973 0.10758 -0.0252 1.0000 0.0176
-8.250 -0.3100 0.10099 0.09893 -0.0234 1.0000 0.0181
-8.000 -0.3066 0.09906 0.09702 -0.0218 1.0000 0.0184
-7.750 -0.2860 0.09576 0.09372 -0.0254 0.9979 0.0189
-7.500 -0.2649 0.09212 0.09008 -0.0303 0.9953 0.0196
-7.250 -0.2464 0.08834 0.08630 -0.0351 0.9916 0.0206
-7.000 -0.2148 0.08184 0.07980 -0.0487 0.9857 0.0227
-6.750 -0.1855 0.07643 0.07437 -0.0581 0.9805 0.0229
-6.500 -0.1662 0.07101 0.06896 -0.0632 0.9763 0.0236
-6.250 -0.1354 0.06776 0.06569 -0.0684 0.9737 0.0243
-6.000 -0.1060 0.06409 0.06200 -0.0744 0.9689 0.0252
-5.750 -0.0042 0.02103 0.01732 -0.1356 0.9603 0.0183
-5.500 0.0302 0.01848 0.01442 -0.1383 0.9552 0.0188
-5.250 0.0645 0.01696 0.01269 -0.1402 0.9498 0.0196
-5.000 0.1039 0.01583 0.01136 -0.1427 0.9466 0.0211
-4.750 0.1329 0.01454 0.00980 -0.1429 0.9368 0.0221
-4.500 0.1707 0.01328 0.00828 -0.1448 0.9314 0.0231
-4.000 0.2375 0.01114 0.00591 -0.1470 0.8985 0.0268
-3.750 0.2861 0.01054 0.00512 -0.1510 0.8745 0.0299
-3.500 0.3263 0.00971 0.00405 -0.1535 0.8401 0.0340
-3.250 0.3561 0.00960 0.00368 -0.1535 0.8109 0.0376
-3.000 0.3835 0.00924 0.00314 -0.1533 0.7884 0.0437
-2.750 0.4105 0.00914 0.00288 -0.1528 0.7708 0.0488
-2.500 0.4376 0.00887 0.00250 -0.1525 0.7555 0.0593
-2.250 0.4646 0.00852 0.00232 -0.1523 0.7416 0.1212
-2.000 0.4916 0.00869 0.00245 -0.1518 0.7279 0.1528
-1.750 0.5184 0.00885 0.00253 -0.1513 0.7139 0.1635
-1.500 0.5452 0.00904 0.00258 -0.1508 0.6989 0.1706
-1.250 0.5717 0.00910 0.00260 -0.1503 0.6834 0.1776
-1.000 0.5983 0.00921 0.00261 -0.1499 0.6684 0.1833
-0.750 0.6248 0.00923 0.00254 -0.1494 0.6528 0.1873
-0.500 0.6509 0.00929 0.00254 -0.1489 0.6348 0.1922
-0.250 0.6769 0.00945 0.00258 -0.1483 0.6137 0.1987
0.000 0.7024 0.00949 0.00251 -0.1477 0.5907 0.2032
0.250 0.7281 0.00956 0.00250 -0.1471 0.5689 0.2065
0.500 0.7540 0.00966 0.00250 -0.1466 0.5486 0.2102
0.750 0.7799 0.00980 0.00252 -0.1460 0.5295 0.2141
1.000 0.8056 0.00987 0.00253 -0.1455 0.5085 0.2186
1.250 0.8313 0.01000 0.00258 -0.1450 0.4858 0.2231
1.500 0.8569 0.01016 0.00264 -0.1445 0.4633 0.2278
1.750 0.8822 0.01033 0.00271 -0.1439 0.4369 0.2330
2.000 0.9074 0.01052 0.00280 -0.1434 0.4102 0.2390
2.250 0.9327 0.01073 0.00292 -0.1429 0.3888 0.2459
2.500 0.9582 0.01090 0.00306 -0.1424 0.3725 0.2554
2.750 0.9838 0.01107 0.00321 -0.1420 0.3600 0.2672
3.000 1.0095 0.01123 0.00338 -0.1416 0.3494 0.2870
3.250 1.0356 0.01132 0.00359 -0.1412 0.3405 0.3399
3.500 1.0614 0.01129 0.00385 -0.1410 0.3324 0.4758
3.750 1.0824 0.01060 0.00401 -0.1395 0.3256 1.0000
4.000 1.1077 0.01085 0.00419 -0.1390 0.3182 1.0000
4.250 1.1338 0.01102 0.00436 -0.1386 0.3122 1.0000
4.500 1.1593 0.01125 0.00455 -0.1381 0.3052 1.0000
4.750 1.1850 0.01145 0.00474 -0.1377 0.2992 1.0000
5.000 1.2106 0.01164 0.00493 -0.1372 0.2924 1.0000
5.250 1.2357 0.01187 0.00515 -0.1367 0.2857 1.0000
5.500 1.2613 0.01207 0.00536 -0.1363 0.2778 1.0000
5.750 1.2862 0.01230 0.00558 -0.1357 0.2696 1.0000
6.000 1.3108 0.01256 0.00581 -0.1351 0.2580 1.0000
6.250 1.3346 0.01288 0.00606 -0.1345 0.2360 1.0000
6.750 1.3770 0.01397 0.00684 -0.1323 0.1867 1.0000
7.000 1.3980 0.01450 0.00730 -0.1312 0.1748 1.0000
7.250 1.4204 0.01490 0.00771 -0.1303 0.1680 1.0000
7.500 1.4415 0.01539 0.00818 -0.1292 0.1608 1.0000
7.750 1.4644 0.01571 0.00855 -0.1284 0.1543 1.0000
8.000 1.4851 0.01621 0.00902 -0.1272 0.1451 1.0000
8.250 1.5064 0.01663 0.00944 -0.1262 0.1307 1.0000
8.500 1.5176 0.01787 0.01036 -0.1236 0.0832 1.0000
8.750 1.5331 0.01871 0.01121 -0.1217 0.0703 1.0000
9.000 1.5383 0.02024 0.01245 -0.1181 0.0276 1.0000
9.250 1.5475 0.02130 0.01353 -0.1149 0.0211 1.0000
9.500 1.5602 0.02210 0.01445 -0.1124 0.0191 1.0000
9.750 1.5711 0.02301 0.01544 -0.1098 0.0176 1.0000
10.000 1.5782 0.02416 0.01668 -0.1066 0.0161 1.0000
10.250 1.5809 0.02561 0.01827 -0.1030 0.0151 1.0000
10.500 1.5892 0.02670 0.01946 -0.1004 0.0146 1.0000
10.750 1.5950 0.02800 0.02087 -0.0975 0.0140 1.0000
11.000 1.5987 0.02949 0.02247 -0.0947 0.0135 1.0000
11.250 1.6007 0.03119 0.02429 -0.0919 0.0130 1.0000
11.500 1.6007 0.03316 0.02637 -0.0893 0.0127 1.0000
11.750 1.5987 0.03547 0.02880 -0.0870 0.0123 1.0000
12.000 1.5937 0.03828 0.03172 -0.0851 0.0120 1.0000
12.250 1.5853 0.04168 0.03526 -0.0835 0.0117 1.0000
12.500 1.5725 0.04582 0.03954 -0.0822 0.0114 1.0000
12.750 1.5563 0.05056 0.04443 -0.0813 0.0112 1.0000
13.000 1.5543 0.05381 0.04780 -0.0810 0.0110 1.0000
13.250 1.5528 0.05708 0.05119 -0.0808 0.0108 1.0000
13.500 1.5489 0.06075 0.05498 -0.0807 0.0106 1.0000
13.750 1.5432 0.06473 0.05908 -0.0808 0.0104 1.0000
14.000 1.5366 0.06889 0.06335 -0.0810 0.0102 1.0000
14.250 1.5297 0.07313 0.06770 -0.0813 0.0101 1.0000
14.500 1.5234 0.07736 0.07204 -0.0816 0.0099 1.0000
14.750 1.5175 0.08160 0.07637 -0.0821 0.0098 1.0000
15.000 1.5118 0.08578 0.08067 -0.0825 0.0096 1.0000
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Polar data table (+)
Polar graphs
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