GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 500,000 Max Cl/Cd: 96.6 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe430-il-500000-n5.txt Download as CSV file: xf-goe430-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 430 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7859 0.07370 0.07058 -0.0755 1.0000 0.0347
-14.750 -0.8224 0.06452 0.06126 -0.0820 1.0000 0.0349
-14.500 -0.8492 0.05734 0.05394 -0.0872 1.0000 0.0351
-14.250 -0.8717 0.05127 0.04776 -0.0914 1.0000 0.0352
-14.000 -0.8965 0.04625 0.04266 -0.0934 1.0000 0.0353
-13.750 -0.8965 0.04097 0.03730 -0.1004 0.9935 0.0358
-13.500 -0.8819 0.03637 0.03260 -0.1085 0.9847 0.0363
-13.250 -0.8594 0.03266 0.02878 -0.1163 0.9772 0.0369
-13.000 -0.8297 0.02967 0.02566 -0.1240 0.9718 0.0376
-12.750 -0.8009 0.02740 0.02325 -0.1299 0.9650 0.0383
-12.500 -0.7718 0.02588 0.02159 -0.1337 0.9602 0.0391
-12.250 -0.7441 0.02469 0.02027 -0.1363 0.9553 0.0398
-12.000 -0.7174 0.02369 0.01913 -0.1381 0.9496 0.0406
-11.750 -0.6889 0.02297 0.01826 -0.1397 0.9451 0.0413
-11.500 -0.6630 0.02194 0.01713 -0.1412 0.9400 0.0422
-11.250 -0.6372 0.02111 0.01625 -0.1422 0.9338 0.0431
-11.000 -0.6102 0.02039 0.01544 -0.1431 0.9282 0.0437
-10.750 -0.5841 0.01966 0.01463 -0.1437 0.9219 0.0441
-10.500 -0.5576 0.01898 0.01384 -0.1443 0.9157 0.0446
-10.250 -0.5304 0.01836 0.01312 -0.1449 0.9111 0.0451
-10.000 -0.5031 0.01779 0.01247 -0.1454 0.9066 0.0457
-9.750 -0.4756 0.01722 0.01181 -0.1460 0.9024 0.0463
-9.500 -0.4479 0.01666 0.01115 -0.1465 0.8983 0.0468
-9.250 -0.4199 0.01614 0.01053 -0.1469 0.8946 0.0473
-9.000 -0.3919 0.01565 0.00996 -0.1474 0.8905 0.0478
-8.750 -0.3637 0.01520 0.00942 -0.1478 0.8861 0.0482
-8.500 -0.3355 0.01479 0.00892 -0.1481 0.8812 0.0486
-8.250 -0.3071 0.01441 0.00845 -0.1485 0.8765 0.0489
-8.000 -0.2788 0.01399 0.00796 -0.1488 0.8707 0.0493
-7.750 -0.2504 0.01341 0.00732 -0.1493 0.8657 0.0503
-7.500 -0.2217 0.01297 0.00682 -0.1497 0.8613 0.0513
-7.250 -0.1928 0.01260 0.00642 -0.1501 0.8558 0.0521
-7.000 -0.1640 0.01227 0.00604 -0.1505 0.8501 0.0529
-6.750 -0.1349 0.01198 0.00568 -0.1508 0.8453 0.0537
-6.500 -0.1058 0.01170 0.00536 -0.1511 0.8398 0.0545
-6.250 -0.0767 0.01144 0.00504 -0.1514 0.8335 0.0554
-6.000 -0.0477 0.01121 0.00474 -0.1516 0.8273 0.0563
-5.750 -0.0186 0.01098 0.00447 -0.1518 0.8196 0.0572
-5.500 0.0104 0.01080 0.00420 -0.1520 0.8119 0.0580
-5.250 0.0397 0.01057 0.00394 -0.1523 0.8036 0.0593
-5.000 0.0689 0.01035 0.00367 -0.1525 0.7961 0.0615
-4.750 0.0982 0.01014 0.00345 -0.1528 0.7881 0.0640
-4.500 0.1273 0.00999 0.00324 -0.1530 0.7800 0.0668
-4.250 0.1566 0.00983 0.00306 -0.1532 0.7708 0.0707
-4.000 0.1858 0.00965 0.00288 -0.1534 0.7614 0.0789
-3.750 0.2148 0.00945 0.00274 -0.1537 0.7503 0.0999
-3.500 0.2438 0.00936 0.00266 -0.1538 0.7385 0.1151
-3.250 0.2725 0.00931 0.00258 -0.1539 0.7259 0.1241
-3.000 0.3010 0.00931 0.00250 -0.1539 0.7127 0.1309
-2.500 0.3581 0.00928 0.00238 -0.1540 0.6862 0.1432
-2.250 0.3864 0.00932 0.00233 -0.1539 0.6715 0.1475
-2.000 0.4146 0.00933 0.00228 -0.1539 0.6561 0.1526
-1.750 0.4427 0.00936 0.00225 -0.1538 0.6409 0.1578
-1.500 0.4708 0.00940 0.00223 -0.1538 0.6277 0.1625
-1.250 0.4990 0.00943 0.00221 -0.1538 0.6157 0.1686
-1.000 0.5274 0.00944 0.00220 -0.1538 0.6035 0.1769
-0.750 0.5558 0.00944 0.00221 -0.1539 0.5917 0.1908
-0.500 0.5842 0.00943 0.00224 -0.1540 0.5804 0.2148
-0.250 0.6125 0.00943 0.00229 -0.1541 0.5692 0.2459
0.000 0.6408 0.00946 0.00234 -0.1541 0.5579 0.2713
0.250 0.6688 0.00952 0.00240 -0.1541 0.5456 0.2907
0.500 0.6965 0.00960 0.00246 -0.1540 0.5309 0.3058
0.750 0.7239 0.00971 0.00253 -0.1538 0.5141 0.3185
1.000 0.7509 0.00985 0.00261 -0.1536 0.4953 0.3308
1.250 0.7777 0.01000 0.00271 -0.1534 0.4773 0.3456
1.500 0.8047 0.01013 0.00283 -0.1532 0.4630 0.3661
1.750 0.8318 0.01025 0.00296 -0.1531 0.4519 0.3913
2.000 0.8593 0.01035 0.00310 -0.1530 0.4422 0.4199
2.250 0.8865 0.01047 0.00325 -0.1528 0.4344 0.4503
2.500 0.9141 0.01056 0.00339 -0.1527 0.4275 0.4746
3.000 0.9684 0.01082 0.00369 -0.1524 0.4127 0.5130
3.250 0.9952 0.01096 0.00386 -0.1521 0.4052 0.5295
3.500 1.0222 0.01108 0.00402 -0.1519 0.3985 0.5483
3.750 1.0493 0.01120 0.00420 -0.1517 0.3915 0.5709
4.000 1.0757 0.01136 0.00440 -0.1514 0.3844 0.5944
4.250 1.1024 0.01149 0.00459 -0.1511 0.3748 0.6165
4.500 1.1283 0.01168 0.00479 -0.1507 0.3625 0.6379
4.750 1.1532 0.01194 0.00502 -0.1502 0.3417 0.6592
5.000 1.1696 0.01286 0.00553 -0.1484 0.2611 0.6763
5.250 1.1899 0.01348 0.00601 -0.1472 0.2321 0.6907
5.500 1.2130 0.01386 0.00637 -0.1463 0.2200 0.7061
5.750 1.2363 0.01417 0.00671 -0.1456 0.2120 0.7267
6.000 1.2600 0.01439 0.00703 -0.1448 0.2064 0.7566
6.250 1.2767 0.01431 0.00728 -0.1424 0.2015 1.0000
6.500 1.3000 0.01465 0.00762 -0.1417 0.1969 1.0000
6.750 1.3235 0.01497 0.00794 -0.1409 0.1907 1.0000
7.000 1.3445 0.01544 0.00835 -0.1398 0.1810 1.0000
7.250 1.3669 0.01578 0.00868 -0.1389 0.1722 1.0000
7.500 1.3877 0.01621 0.00908 -0.1378 0.1637 1.0000
7.750 1.4071 0.01666 0.00948 -0.1364 0.1523 1.0000
8.000 1.4235 0.01720 0.00995 -0.1345 0.1371 1.0000
8.250 1.4379 0.01790 0.01053 -0.1324 0.1170 1.0000
8.750 1.4648 0.01944 0.01192 -0.1280 0.0925 1.0000
9.000 1.4788 0.02019 0.01265 -0.1261 0.0865 1.0000
9.250 1.4949 0.02082 0.01330 -0.1244 0.0836 1.0000
9.500 1.5097 0.02154 0.01405 -0.1227 0.0804 1.0000
9.750 1.5225 0.02241 0.01492 -0.1207 0.0764 1.0000
10.000 1.5372 0.02318 0.01573 -0.1191 0.0735 1.0000
10.250 1.5526 0.02391 0.01651 -0.1176 0.0705 1.0000
10.500 1.5652 0.02484 0.01746 -0.1158 0.0659 1.0000
10.750 1.5774 0.02584 0.01847 -0.1141 0.0603 1.0000
11.000 1.5729 0.02810 0.02049 -0.1108 0.0305 1.0000
11.250 1.5740 0.03004 0.02242 -0.1082 0.0223 1.0000
11.500 1.5801 0.03164 0.02406 -0.1062 0.0193 1.0000
11.750 1.5880 0.03313 0.02560 -0.1045 0.0177 1.0000
12.000 1.5951 0.03473 0.02726 -0.1029 0.0165 1.0000
12.250 1.6011 0.03647 0.02906 -0.1013 0.0155 1.0000
12.500 1.6082 0.03815 0.03082 -0.0998 0.0149 1.0000
12.750 1.6147 0.03993 0.03268 -0.0984 0.0143 1.0000
13.000 1.6200 0.04186 0.03468 -0.0971 0.0138 1.0000
13.250 1.6242 0.04396 0.03685 -0.0959 0.0133 1.0000
13.500 1.6272 0.04624 0.03922 -0.0947 0.0129 1.0000
13.750 1.6283 0.04881 0.04186 -0.0936 0.0124 1.0000
14.000 1.6304 0.05137 0.04450 -0.0927 0.0121 1.0000
14.250 1.6333 0.05389 0.04712 -0.0920 0.0118 1.0000
14.500 1.6351 0.05659 0.04992 -0.0913 0.0115 1.0000
14.750 1.6360 0.05946 0.05289 -0.0908 0.0112 1.0000
15.000 1.6360 0.06252 0.05604 -0.0903 0.0109 1.0000
15.250 1.6351 0.06575 0.05936 -0.0900 0.0107 1.0000
15.500 1.6331 0.06915 0.06285 -0.0898 0.0105 1.0000
15.750 1.6301 0.07275 0.06655 -0.0898 0.0103 1.0000
16.000 1.6258 0.07659 0.07049 -0.0899 0.0101 1.0000
16.250 1.6202 0.08069 0.07470 -0.0901 0.0099 1.0000
16.500 1.6130 0.08508 0.07919 -0.0905 0.0098 1.0000
16.750 1.6043 0.08975 0.08398 -0.0912 0.0096 1.0000
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