GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 500,000 Max Cl/Cd: 113.01 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe239-il-500000-n5.txt Download as CSV file: xf-goe239-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 239 (MVA H.31) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3165 0.12580 0.12335 -0.0394 1.0000 0.0124
-12.000 -0.3109 0.12315 0.12072 -0.0402 1.0000 0.0126
-10.500 -0.4784 0.02749 0.02414 -0.1350 0.9218 0.0209
-10.250 -0.4517 0.02424 0.02047 -0.1396 0.9134 0.0217
-10.000 -0.4252 0.02221 0.01806 -0.1420 0.9056 0.0224
-9.750 -0.3983 0.02109 0.01680 -0.1432 0.8996 0.0230
-9.500 -0.3709 0.02058 0.01622 -0.1437 0.8936 0.0235
-9.250 -0.3433 0.02006 0.01561 -0.1443 0.8879 0.0241
-9.000 -0.3158 0.01937 0.01478 -0.1449 0.8823 0.0247
-8.750 -0.2883 0.01861 0.01386 -0.1455 0.8765 0.0255
-8.500 -0.2607 0.01784 0.01287 -0.1460 0.8707 0.0263
-8.250 -0.2328 0.01714 0.01197 -0.1465 0.8646 0.0269
-8.000 -0.2051 0.01631 0.01097 -0.1469 0.8578 0.0275
-7.750 -0.1774 0.01569 0.01026 -0.1473 0.8513 0.0282
-7.500 -0.1493 0.01527 0.00976 -0.1475 0.8444 0.0289
-7.250 -0.1210 0.01481 0.00920 -0.1478 0.8388 0.0295
-7.000 -0.0925 0.01434 0.00863 -0.1480 0.8333 0.0301
-6.750 -0.0640 0.01391 0.00810 -0.1483 0.8271 0.0309
-6.500 -0.0355 0.01349 0.00754 -0.1485 0.8211 0.0316
-6.250 -0.0067 0.01304 0.00699 -0.1487 0.8139 0.0322
-6.000 0.0218 0.01268 0.00650 -0.1488 0.8060 0.0326
-5.750 0.0505 0.01218 0.00592 -0.1491 0.7973 0.0332
-5.500 0.0791 0.01179 0.00546 -0.1493 0.7882 0.0342
-5.250 0.1078 0.01151 0.00512 -0.1494 0.7777 0.0350
-5.000 0.1365 0.01125 0.00479 -0.1495 0.7660 0.0358
-4.750 0.1650 0.01102 0.00445 -0.1496 0.7517 0.0366
-4.500 0.1933 0.01082 0.00414 -0.1496 0.7324 0.0375
-4.250 0.2210 0.01069 0.00385 -0.1494 0.7056 0.0384
-4.000 0.2481 0.01064 0.00359 -0.1491 0.6702 0.0392
-3.750 0.2752 0.01059 0.00334 -0.1489 0.6367 0.0404
-3.500 0.3026 0.01055 0.00317 -0.1488 0.6113 0.0423
-3.250 0.3304 0.01054 0.00303 -0.1487 0.5923 0.0443
-3.000 0.3584 0.01052 0.00290 -0.1487 0.5781 0.0463
-2.750 0.3867 0.01048 0.00278 -0.1487 0.5671 0.0487
-2.500 0.4152 0.01041 0.00267 -0.1488 0.5589 0.0529
-2.250 0.4436 0.01039 0.00259 -0.1488 0.5513 0.0574
-2.000 0.4721 0.01033 0.00253 -0.1489 0.5451 0.0654
-1.750 0.5007 0.01028 0.00248 -0.1490 0.5392 0.0765
-1.500 0.5290 0.01026 0.00245 -0.1491 0.5336 0.0898
-1.250 0.5575 0.01022 0.00240 -0.1491 0.5284 0.1041
-1.000 0.5861 0.01012 0.00237 -0.1493 0.5229 0.1316
-0.750 0.6144 0.01005 0.00243 -0.1494 0.5176 0.1962
-0.500 0.6426 0.01008 0.00247 -0.1495 0.5130 0.2158
-0.250 0.6711 0.01009 0.00251 -0.1495 0.5079 0.2330
0.000 0.6990 0.01014 0.00256 -0.1495 0.5016 0.2451
0.250 0.7271 0.01019 0.00261 -0.1495 0.4959 0.2560
0.500 0.7554 0.01022 0.00266 -0.1495 0.4910 0.2687
1.000 0.8115 0.01033 0.00280 -0.1495 0.4834 0.2933
1.250 0.8396 0.01038 0.00288 -0.1495 0.4799 0.3075
1.500 0.8678 0.01042 0.00296 -0.1495 0.4758 0.3207
1.750 0.8958 0.01048 0.00304 -0.1495 0.4712 0.3348
2.000 0.9234 0.01056 0.00314 -0.1494 0.4670 0.3504
2.250 0.9513 0.01063 0.00324 -0.1494 0.4632 0.3636
2.500 0.9793 0.01068 0.00334 -0.1494 0.4590 0.3753
2.750 1.0070 0.01075 0.00344 -0.1493 0.4543 0.3868
3.000 1.0343 0.01084 0.00355 -0.1492 0.4497 0.3987
3.250 1.0620 0.01090 0.00366 -0.1492 0.4450 0.4121
3.500 1.0896 0.01096 0.00378 -0.1491 0.4394 0.4287
3.750 1.1167 0.01104 0.00392 -0.1490 0.4336 0.4546
4.000 1.1445 0.01073 0.00416 -0.1493 0.4273 0.6845
4.250 1.1638 0.01034 0.00424 -0.1472 0.4192 1.0000
4.500 1.1900 0.01053 0.00437 -0.1469 0.4044 1.0000
4.750 1.2150 0.01080 0.00454 -0.1465 0.3836 1.0000
5.000 1.2399 0.01110 0.00474 -0.1460 0.3649 1.0000
5.250 1.2648 0.01139 0.00497 -0.1455 0.3510 1.0000
5.500 1.2896 0.01169 0.00522 -0.1450 0.3386 1.0000
6.000 1.3382 0.01235 0.00577 -0.1439 0.3130 1.0000
6.250 1.3622 0.01269 0.00607 -0.1433 0.3012 1.0000
6.500 1.3860 0.01302 0.00639 -0.1427 0.2915 1.0000
6.750 1.4098 0.01336 0.00670 -0.1420 0.2822 1.0000
7.000 1.4334 0.01369 0.00702 -0.1414 0.2737 1.0000
7.250 1.4558 0.01410 0.00740 -0.1405 0.2628 1.0000
7.500 1.4782 0.01448 0.00777 -0.1397 0.2517 1.0000
7.750 1.5004 0.01487 0.00815 -0.1388 0.2427 1.0000
8.000 1.5208 0.01536 0.00859 -0.1377 0.2295 1.0000
8.250 1.5403 0.01590 0.00908 -0.1364 0.2145 1.0000
8.500 1.5589 0.01645 0.00958 -0.1350 0.1988 1.0000
8.750 1.5740 0.01720 0.01021 -0.1331 0.1734 1.0000
9.000 1.5739 0.01871 0.01136 -0.1287 0.1216 1.0000
9.250 1.5821 0.01971 0.01228 -0.1257 0.1042 1.0000
9.500 1.5911 0.02070 0.01322 -0.1229 0.0863 1.0000
9.750 1.5931 0.02216 0.01452 -0.1194 0.0627 1.0000
10.000 1.6029 0.02316 0.01553 -0.1170 0.0560 1.0000
10.250 1.6136 0.02415 0.01655 -0.1149 0.0521 1.0000
10.500 1.6236 0.02522 0.01766 -0.1128 0.0486 1.0000
10.750 1.6361 0.02615 0.01866 -0.1112 0.0464 1.0000
11.000 1.6465 0.02725 0.01983 -0.1094 0.0436 1.0000
11.250 1.6542 0.02860 0.02122 -0.1074 0.0407 1.0000
11.500 1.6638 0.02985 0.02253 -0.1057 0.0380 1.0000
11.750 1.6714 0.03129 0.02401 -0.1040 0.0343 1.0000
12.000 1.6775 0.03291 0.02567 -0.1023 0.0306 1.0000
12.250 1.6816 0.03476 0.02755 -0.1006 0.0258 1.0000
12.500 1.6834 0.03688 0.02969 -0.0988 0.0215 1.0000
12.750 1.6845 0.03916 0.03201 -0.0973 0.0187 1.0000
13.000 1.6851 0.04157 0.03450 -0.0959 0.0170 1.0000
13.250 1.6850 0.04416 0.03716 -0.0946 0.0157 1.0000
13.500 1.6830 0.04705 0.04013 -0.0936 0.0147 1.0000
13.750 1.6811 0.05008 0.04326 -0.0927 0.0139 1.0000
14.000 1.6799 0.05316 0.04645 -0.0921 0.0133 1.0000
14.250 1.6773 0.05650 0.04991 -0.0917 0.0127 1.0000
14.500 1.6735 0.06013 0.05364 -0.0915 0.0122 1.0000
14.750 1.6683 0.06404 0.05765 -0.0915 0.0118 1.0000
15.000 1.6617 0.06821 0.06192 -0.0916 0.0114 1.0000
15.250 1.6549 0.07242 0.06624 -0.0917 0.0110 1.0000
15.500 1.6499 0.07644 0.07038 -0.0920 0.0108 1.0000
15.750 1.6438 0.08064 0.07469 -0.0923 0.0105 1.0000
16.000 1.6370 0.08495 0.07911 -0.0927 0.0103 1.0000
16.250 1.6294 0.08940 0.08368 -0.0932 0.0100 1.0000
16.500 1.6216 0.09395 0.08833 -0.0939 0.0098 1.0000
16.750 1.6135 0.09861 0.09309 -0.0946 0.0096 1.0000
17.000 1.6054 0.10331 0.09790 -0.0955 0.0094 1.0000
17.250 1.5971 0.10808 0.10278 -0.0965 0.0092 1.0000
17.500 1.5886 0.11294 0.10774 -0.0977 0.0090 1.0000
17.750 1.5798 0.11795 0.11284 -0.0990 0.0089 1.0000
18.000 1.5707 0.12307 0.11806 -0.1006 0.0087 1.0000
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