GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.3 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe239-il-1000000.txt Download as CSV file: xf-goe239-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3161 0.13306 0.13132 -0.0373 1.0000 0.0175
-12.250 -0.3136 0.12898 0.12724 -0.0387 1.0000 0.0176
-11.500 -0.6148 0.03097 0.02861 -0.1236 0.9765 0.0191
-11.250 -0.5789 0.02662 0.02403 -0.1322 0.9714 0.0197
-11.000 -0.5494 0.02461 0.02182 -0.1357 0.9619 0.0203
-10.750 -0.5195 0.02302 0.02003 -0.1383 0.9534 0.0208
-10.500 -0.4905 0.02195 0.01878 -0.1400 0.9444 0.0212
-10.250 -0.4662 0.01933 0.01585 -0.1423 0.9338 0.0219
-10.000 -0.4390 0.01879 0.01523 -0.1428 0.9253 0.0223
-9.750 -0.4117 0.01840 0.01478 -0.1430 0.9176 0.0228
-9.500 -0.3841 0.01803 0.01433 -0.1433 0.9112 0.0233
-9.250 -0.3567 0.01757 0.01377 -0.1436 0.9044 0.0239
-9.000 -0.3293 0.01703 0.01307 -0.1439 0.8979 0.0246
-8.750 -0.3015 0.01648 0.01240 -0.1443 0.8922 0.0251
-8.500 -0.2734 0.01615 0.01194 -0.1445 0.8860 0.0254
-8.250 -0.2472 0.01445 0.01002 -0.1453 0.8801 0.0264
-8.000 -0.2190 0.01412 0.00967 -0.1455 0.8745 0.0270
-7.750 -0.1907 0.01383 0.00932 -0.1456 0.8690 0.0277
-7.500 -0.1624 0.01342 0.00881 -0.1458 0.8642 0.0283
-7.250 -0.1338 0.01296 0.00827 -0.1461 0.8594 0.0289
-7.000 -0.1051 0.01260 0.00781 -0.1463 0.8540 0.0296
-6.750 -0.0765 0.01240 0.00751 -0.1463 0.8485 0.0301
-6.500 -0.0479 0.01149 0.00649 -0.1468 0.8430 0.0309
-6.250 -0.0192 0.01092 0.00586 -0.1471 0.8370 0.0317
-6.000 0.0095 0.01061 0.00549 -0.1472 0.8313 0.0323
-5.750 0.0386 0.01035 0.00520 -0.1474 0.8250 0.0331
-5.500 0.0674 0.01010 0.00489 -0.1475 0.8181 0.0340
-5.250 0.0965 0.00982 0.00455 -0.1477 0.8108 0.0347
-5.000 0.1254 0.00959 0.00425 -0.1478 0.8018 0.0354
-4.750 0.1544 0.00941 0.00400 -0.1479 0.7922 0.0358
-4.500 0.1834 0.00894 0.00343 -0.1481 0.7810 0.0371
-4.250 0.2122 0.00872 0.00316 -0.1482 0.7673 0.0384
-4.000 0.2408 0.00859 0.00295 -0.1482 0.7493 0.0396
-3.750 0.2690 0.00851 0.00274 -0.1481 0.7220 0.0409
-3.500 0.2961 0.00855 0.00258 -0.1478 0.6788 0.0420
-3.250 0.3229 0.00863 0.00242 -0.1475 0.6322 0.0434
-3.000 0.3506 0.00862 0.00226 -0.1475 0.6011 0.0462
-2.750 0.3787 0.00865 0.00219 -0.1474 0.5818 0.0489
-2.500 0.4072 0.00862 0.00208 -0.1475 0.5691 0.0530
-2.250 0.4357 0.00860 0.00202 -0.1475 0.5589 0.0592
-2.000 0.4646 0.00852 0.00195 -0.1476 0.5508 0.0699
-1.750 0.4930 0.00851 0.00191 -0.1477 0.5431 0.0839
-1.500 0.5221 0.00842 0.00186 -0.1479 0.5374 0.1013
-1.250 0.5510 0.00824 0.00181 -0.1481 0.5316 0.1527
-1.000 0.5795 0.00820 0.00186 -0.1483 0.5253 0.2031
-0.750 0.6083 0.00820 0.00188 -0.1484 0.5195 0.2189
-0.500 0.6367 0.00823 0.00191 -0.1484 0.5142 0.2312
-0.250 0.6650 0.00829 0.00195 -0.1484 0.5099 0.2416
0.000 0.6940 0.00829 0.00197 -0.1485 0.5068 0.2530
0.250 0.7227 0.00829 0.00201 -0.1486 0.5029 0.2660
0.500 0.7511 0.00833 0.00206 -0.1487 0.4990 0.2775
0.750 0.7793 0.00839 0.00212 -0.1487 0.4950 0.2913
1.000 0.8079 0.00841 0.00219 -0.1488 0.4919 0.3083
1.250 0.8366 0.00842 0.00224 -0.1489 0.4888 0.3248
1.500 0.8651 0.00845 0.00231 -0.1489 0.4852 0.3397
1.750 0.8933 0.00851 0.00238 -0.1489 0.4814 0.3540
2.000 0.9211 0.00861 0.00247 -0.1489 0.4772 0.3691
2.250 0.9498 0.00861 0.00254 -0.1490 0.4742 0.3844
2.500 0.9783 0.00863 0.00261 -0.1491 0.4703 0.3981
2.750 1.0064 0.00868 0.00268 -0.1491 0.4654 0.4116
3.000 1.0341 0.00875 0.00277 -0.1490 0.4600 0.4279
3.250 1.0626 0.00874 0.00285 -0.1492 0.4549 0.4538
3.500 1.0912 0.00845 0.00303 -0.1496 0.4490 0.6737
3.750 1.1122 0.00797 0.00312 -0.1480 0.4430 1.0000
4.000 1.1402 0.00806 0.00320 -0.1479 0.4354 1.0000
4.250 1.1675 0.00820 0.00330 -0.1478 0.4277 1.0000
4.500 1.1951 0.00831 0.00340 -0.1478 0.4180 1.0000
4.750 1.2222 0.00847 0.00351 -0.1476 0.4072 1.0000
5.000 1.2488 0.00866 0.00365 -0.1474 0.3943 1.0000
5.250 1.2751 0.00887 0.00380 -0.1472 0.3811 1.0000
5.500 1.3009 0.00911 0.00399 -0.1468 0.3669 1.0000
5.750 1.3264 0.00939 0.00419 -0.1465 0.3514 1.0000
6.000 1.3515 0.00969 0.00442 -0.1460 0.3357 1.0000
6.250 1.3764 0.01000 0.00467 -0.1455 0.3216 1.0000
6.500 1.4013 0.01030 0.00492 -0.1451 0.3083 1.0000
6.750 1.4257 0.01063 0.00519 -0.1446 0.2944 1.0000
7.000 1.4499 0.01097 0.00547 -0.1440 0.2805 1.0000
7.250 1.4738 0.01132 0.00577 -0.1434 0.2669 1.0000
7.500 1.4972 0.01170 0.00608 -0.1427 0.2524 1.0000
7.750 1.5201 0.01210 0.00642 -0.1420 0.2381 1.0000
8.000 1.5428 0.01250 0.00677 -0.1412 0.2247 1.0000
8.250 1.5646 0.01295 0.00715 -0.1403 0.2090 1.0000
8.500 1.5845 0.01353 0.00760 -0.1391 0.1882 1.0000
8.750 1.5963 0.01468 0.00842 -0.1366 0.1376 1.0000
9.000 1.6067 0.01583 0.00937 -0.1339 0.1049 1.0000
9.250 1.6181 0.01680 0.01019 -0.1313 0.0786 1.0000
9.500 1.6265 0.01778 0.01103 -0.1282 0.0593 1.0000
9.750 1.6386 0.01847 0.01171 -0.1256 0.0541 1.0000
10.000 1.6525 0.01908 0.01235 -0.1234 0.0501 1.0000
10.250 1.6667 0.01971 0.01301 -0.1214 0.0473 1.0000
10.500 1.6784 0.02050 0.01381 -0.1190 0.0438 1.0000
10.750 1.6924 0.02117 0.01452 -0.1172 0.0411 1.0000
11.000 1.7047 0.02197 0.01534 -0.1151 0.0377 1.0000
11.250 1.7155 0.02291 0.01629 -0.1130 0.0335 1.0000
11.500 1.7241 0.02402 0.01739 -0.1108 0.0281 1.0000
11.750 1.7314 0.02529 0.01865 -0.1085 0.0232 1.0000
12.000 1.7378 0.02668 0.02004 -0.1063 0.0202 1.0000
12.250 1.7449 0.02807 0.02149 -0.1043 0.0184 1.0000
12.500 1.7506 0.02963 0.02309 -0.1024 0.0171 1.0000
12.750 1.7530 0.03152 0.02504 -0.1003 0.0159 1.0000
13.000 1.7591 0.03316 0.02676 -0.0986 0.0153 1.0000
13.250 1.7638 0.03500 0.02867 -0.0970 0.0147 1.0000
13.500 1.7663 0.03707 0.03082 -0.0955 0.0141 1.0000
13.750 1.7667 0.03945 0.03326 -0.0940 0.0136 1.0000
14.000 1.7630 0.04235 0.03625 -0.0925 0.0130 1.0000
14.250 1.7591 0.04541 0.03941 -0.0913 0.0126 1.0000
14.500 1.7601 0.04806 0.04216 -0.0905 0.0124 1.0000
14.750 1.7592 0.05106 0.04525 -0.0899 0.0121 1.0000
15.000 1.7571 0.05433 0.04861 -0.0895 0.0118 1.0000
15.250 1.7533 0.05789 0.05227 -0.0892 0.0115 1.0000
15.500 1.7487 0.06166 0.05614 -0.0891 0.0113 1.0000
15.750 1.7424 0.06575 0.06033 -0.0892 0.0111 1.0000
16.000 1.7344 0.07012 0.06479 -0.0894 0.0109 1.0000
16.250 1.7240 0.07482 0.06960 -0.0898 0.0107 1.0000
16.500 1.7113 0.07990 0.07478 -0.0902 0.0105 1.0000
16.750 1.6959 0.08544 0.08044 -0.0909 0.0103 1.0000
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