GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 100,000 Max Cl/Cd: 60.45 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe428-il-100000-n5.txt Download as CSV file: xf-goe428-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 428 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2764 0.09899 0.09455 -0.0315 1.0000 0.0371
-7.500 -0.2887 0.09841 0.09410 -0.0302 1.0000 0.0377
-7.250 -0.3014 0.09759 0.09341 -0.0281 1.0000 0.0379
-7.000 -0.3046 0.09593 0.09184 -0.0294 0.9982 0.0381
-6.750 -0.2750 0.09138 0.08724 -0.0399 0.9887 0.0384
-6.500 -0.2471 0.08667 0.08248 -0.0482 0.9801 0.0386
-6.250 -0.2199 0.08190 0.07767 -0.0552 0.9716 0.0386
-6.000 -0.1915 0.07704 0.07274 -0.0618 0.9639 0.0387
-5.750 -0.1791 0.07135 0.06712 -0.0626 0.9568 0.0397
-5.500 -0.1548 0.06697 0.06270 -0.0668 0.9486 0.0402
-5.000 -0.0856 0.05546 0.05087 -0.0811 0.9321 0.0264
-4.750 -0.0605 0.05239 0.04779 -0.0841 0.9263 0.0305
-4.500 -0.0286 0.04792 0.04313 -0.0894 0.9163 0.0308
-4.250 0.0168 0.04034 0.03508 -0.0976 0.9092 0.0280
-4.000 0.0517 0.03523 0.02955 -0.1013 0.9006 0.0276
-3.750 0.0846 0.03111 0.02499 -0.1041 0.8928 0.0282
-3.500 0.1166 0.02939 0.02306 -0.1060 0.8849 0.0320
-3.250 0.1497 0.02596 0.01901 -0.1074 0.8753 0.0343
-3.000 0.1849 0.02283 0.01511 -0.1085 0.8654 0.0367
-2.750 0.2182 0.02090 0.01271 -0.1094 0.8537 0.0421
-2.500 0.2507 0.01936 0.01076 -0.1097 0.8414 0.0463
-2.250 0.2807 0.01826 0.00933 -0.1097 0.8286 0.0537
-2.000 0.3093 0.01738 0.00831 -0.1095 0.8165 0.0585
-1.750 0.3377 0.01682 0.00752 -0.1093 0.8051 0.0663
-1.500 0.3657 0.01623 0.00687 -0.1091 0.7942 0.0722
-1.250 0.3940 0.01575 0.00623 -0.1088 0.7835 0.0792
-1.000 0.4212 0.01540 0.00585 -0.1084 0.7716 0.0940
-0.750 0.4479 0.01514 0.00559 -0.1079 0.7595 0.1300
-0.500 0.4749 0.01495 0.00533 -0.1076 0.7474 0.1661
-0.250 0.5021 0.01454 0.00519 -0.1075 0.7354 0.2498
0.000 0.5385 0.01277 0.00503 -0.1090 0.7237 1.0000
0.250 0.5650 0.01287 0.00487 -0.1085 0.7111 1.0000
0.500 0.5912 0.01298 0.00475 -0.1079 0.6978 1.0000
0.750 0.6171 0.01309 0.00467 -0.1073 0.6842 1.0000
1.000 0.6430 0.01322 0.00462 -0.1067 0.6706 1.0000
1.250 0.6688 0.01337 0.00461 -0.1061 0.6570 1.0000
1.500 0.6944 0.01352 0.00462 -0.1055 0.6430 1.0000
1.750 0.7199 0.01369 0.00465 -0.1049 0.6285 1.0000
2.000 0.7452 0.01387 0.00472 -0.1043 0.6138 1.0000
2.250 0.7704 0.01407 0.00481 -0.1037 0.5988 1.0000
2.500 0.7954 0.01429 0.00492 -0.1030 0.5838 1.0000
2.750 0.8203 0.01451 0.00509 -0.1024 0.5689 1.0000
3.000 0.8451 0.01475 0.00525 -0.1017 0.5538 1.0000
3.250 0.8697 0.01500 0.00544 -0.1011 0.5387 1.0000
3.500 0.8941 0.01527 0.00564 -0.1004 0.5239 1.0000
3.750 0.9185 0.01555 0.00590 -0.0997 0.5096 1.0000
4.000 0.9428 0.01585 0.00616 -0.0991 0.4958 1.0000
4.250 0.9670 0.01616 0.00645 -0.0984 0.4826 1.0000
4.500 0.9912 0.01649 0.00680 -0.0978 0.4704 1.0000
4.750 1.0152 0.01684 0.00715 -0.0971 0.4587 1.0000
5.000 1.0391 0.01721 0.00751 -0.0964 0.4480 1.0000
5.250 1.0632 0.01760 0.00792 -0.0958 0.4384 1.0000
5.500 1.0875 0.01799 0.00842 -0.0952 0.4299 1.0000
5.750 1.1119 0.01841 0.00889 -0.0947 0.4233 1.0000
6.000 1.1360 0.01882 0.00944 -0.0941 0.4153 1.0000
6.250 1.1598 0.01926 0.00993 -0.0935 0.4072 1.0000
6.500 1.1827 0.01968 0.01056 -0.0927 0.3975 1.0000
6.750 1.2040 0.02009 0.01108 -0.0916 0.3841 1.0000
7.000 1.2199 0.02048 0.01146 -0.0896 0.3566 1.0000
7.250 1.2347 0.02095 0.01192 -0.0875 0.3252 1.0000
7.500 1.2493 0.02153 0.01248 -0.0855 0.2905 1.0000
7.750 1.2587 0.02253 0.01323 -0.0828 0.2056 1.0000
8.000 1.2485 0.02560 0.01521 -0.0783 0.0845 1.0000
8.250 1.2464 0.02796 0.01719 -0.0746 0.0339 1.0000
8.500 1.2518 0.02941 0.01878 -0.0714 0.0289 1.0000
8.750 1.2543 0.03100 0.02054 -0.0682 0.0258 1.0000
9.000 1.2533 0.03284 0.02255 -0.0648 0.0234 1.0000
9.250 1.2559 0.03448 0.02442 -0.0622 0.0219 1.0000
9.500 1.2558 0.03640 0.02656 -0.0596 0.0211 1.0000
9.750 1.2538 0.03859 0.02897 -0.0573 0.0203 1.0000
10.000 1.2506 0.04105 0.03162 -0.0553 0.0197 1.0000
10.250 1.2471 0.04371 0.03446 -0.0538 0.0190 1.0000
10.500 1.2433 0.04658 0.03749 -0.0525 0.0181 1.0000
10.750 1.2398 0.04957 0.04062 -0.0516 0.0173 1.0000
11.000 1.2365 0.05266 0.04383 -0.0508 0.0164 1.0000
11.250 1.2346 0.05570 0.04696 -0.0500 0.0158 1.0000
11.500 1.2356 0.05855 0.04987 -0.0488 0.0152 1.0000
11.750 1.2443 0.06079 0.05215 -0.0470 0.0147 1.0000
12.000 1.2696 0.06283 0.05429 -0.0442 0.0141 1.0000
12.250 1.2792 0.06549 0.05717 -0.0433 0.0140 1.0000
12.500 1.2836 0.06845 0.06038 -0.0427 0.0137 1.0000
12.750 1.2838 0.07169 0.06388 -0.0425 0.0133 1.0000
13.000 1.2829 0.07523 0.06768 -0.0424 0.0130 1.0000
13.250 1.2792 0.07910 0.07181 -0.0427 0.0127 1.0000
13.500 1.2736 0.08330 0.07627 -0.0434 0.0123 1.0000
13.750 1.2667 0.08787 0.08109 -0.0443 0.0122 1.0000
14.000 1.2579 0.09279 0.08626 -0.0457 0.0120 1.0000
14.250 1.2477 0.09811 0.09183 -0.0475 0.0120 1.0000
14.500 1.2365 0.10381 0.09776 -0.0498 0.0120 1.0000
14.750 1.2239 0.10998 0.10416 -0.0527 0.0120 1.0000
15.000 1.2112 0.11642 0.11082 -0.0560 0.0121 1.0000
15.250 1.1980 0.12329 0.11789 -0.0599 0.0121 1.0000
15.500 1.1845 0.13058 0.12537 -0.0643 0.0122 1.0000
15.750 1.1709 0.13828 0.13326 -0.0691 0.0123 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 428 AIRFOIL (goe428-il)