GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.77 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe430-il-1000000-n5.txt Download as CSV file: xf-goe430-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7306 0.12681 0.12469 -0.0429 1.0000 0.0223
-17.500 -0.7890 0.11219 0.10992 -0.0514 1.0000 0.0232
-17.250 -0.8213 0.10281 0.10045 -0.0570 1.0000 0.0240
-17.000 -0.8504 0.09424 0.09179 -0.0624 1.0000 0.0245
-16.750 -0.8806 0.08573 0.08318 -0.0679 1.0000 0.0249
-16.500 -0.9140 0.07695 0.07429 -0.0738 1.0000 0.0252
-16.250 -0.9568 0.06712 0.06433 -0.0806 1.0000 0.0251
-16.000 -1.0064 0.05675 0.05381 -0.0882 1.0000 0.0249
-15.750 -1.0561 0.04676 0.04367 -0.0957 1.0000 0.0245
-15.250 -1.0890 0.03067 0.02723 -0.1153 0.9872 0.0253
-15.000 -1.0625 0.02597 0.02240 -0.1258 0.9794 0.0266
-14.750 -1.0319 0.02355 0.01986 -0.1321 0.9727 0.0281
-14.500 -1.0045 0.02226 0.01848 -0.1349 0.9661 0.0292
-14.250 -0.9771 0.02124 0.01735 -0.1369 0.9593 0.0299
-14.000 -0.9509 0.02032 0.01635 -0.1384 0.9520 0.0307
-13.750 -0.9245 0.01961 0.01559 -0.1394 0.9449 0.0316
-13.500 -0.8979 0.01903 0.01496 -0.1402 0.9388 0.0325
-13.250 -0.8713 0.01847 0.01434 -0.1409 0.9329 0.0332
-12.750 -0.8176 0.01744 0.01314 -0.1421 0.9224 0.0344
-12.500 -0.7905 0.01699 0.01261 -0.1426 0.9167 0.0349
-12.000 -0.7361 0.01601 0.01147 -0.1436 0.9062 0.0359
-11.750 -0.7087 0.01551 0.01092 -0.1442 0.9008 0.0366
-11.500 -0.6810 0.01515 0.01051 -0.1445 0.8956 0.0374
-11.250 -0.6529 0.01483 0.01016 -0.1449 0.8910 0.0381
-11.000 -0.6247 0.01454 0.00982 -0.1453 0.8863 0.0387
-10.750 -0.5964 0.01429 0.00953 -0.1456 0.8822 0.0395
-10.500 -0.5680 0.01402 0.00920 -0.1459 0.8786 0.0402
-10.250 -0.5394 0.01369 0.00881 -0.1464 0.8753 0.0406
-10.000 -0.5107 0.01336 0.00843 -0.1468 0.8717 0.0409
-9.750 -0.4821 0.01303 0.00803 -0.1472 0.8674 0.0412
-9.500 -0.4536 0.01272 0.00765 -0.1475 0.8627 0.0414
-9.250 -0.4248 0.01242 0.00729 -0.1478 0.8580 0.0416
-9.000 -0.3961 0.01193 0.00673 -0.1484 0.8528 0.0422
-8.750 -0.3672 0.01154 0.00627 -0.1488 0.8481 0.0428
-8.500 -0.3382 0.01122 0.00590 -0.1492 0.8441 0.0434
-8.250 -0.3089 0.01093 0.00558 -0.1496 0.8398 0.0439
-8.000 -0.2798 0.01067 0.00528 -0.1500 0.8344 0.0444
-7.750 -0.2507 0.01045 0.00500 -0.1502 0.8288 0.0450
-7.500 -0.2213 0.01022 0.00474 -0.1506 0.8237 0.0455
-7.250 -0.1920 0.01002 0.00450 -0.1509 0.8174 0.0462
-7.000 -0.1629 0.00984 0.00426 -0.1511 0.8110 0.0468
-6.750 -0.1335 0.00966 0.00404 -0.1514 0.8039 0.0474
-6.500 -0.1043 0.00950 0.00382 -0.1516 0.7963 0.0479
-6.250 -0.0750 0.00934 0.00362 -0.1519 0.7878 0.0484
-6.000 -0.0459 0.00922 0.00343 -0.1521 0.7782 0.0488
-5.750 -0.0166 0.00910 0.00325 -0.1523 0.7677 0.0491
-5.500 0.0127 0.00893 0.00302 -0.1525 0.7581 0.0502
-5.250 0.0418 0.00879 0.00282 -0.1527 0.7470 0.0515
-5.000 0.0710 0.00868 0.00266 -0.1529 0.7341 0.0527
-4.750 0.1000 0.00859 0.00251 -0.1531 0.7204 0.0540
-4.500 0.1290 0.00852 0.00238 -0.1532 0.7061 0.0553
-4.250 0.1579 0.00847 0.00226 -0.1534 0.6922 0.0566
-4.000 0.1868 0.00844 0.00216 -0.1535 0.6788 0.0580
-3.750 0.2157 0.00840 0.00207 -0.1536 0.6658 0.0608
-3.500 0.2447 0.00834 0.00197 -0.1538 0.6532 0.0649
-3.250 0.2736 0.00828 0.00188 -0.1540 0.6395 0.0727
-3.000 0.3026 0.00815 0.00181 -0.1542 0.6255 0.0989
-2.750 0.3314 0.00813 0.00178 -0.1544 0.6124 0.1139
-2.250 0.3891 0.00815 0.00175 -0.1546 0.5883 0.1276
-2.000 0.4178 0.00819 0.00174 -0.1547 0.5769 0.1319
-1.750 0.4465 0.00821 0.00174 -0.1548 0.5642 0.1376
-1.500 0.4752 0.00825 0.00173 -0.1548 0.5516 0.1422
-1.250 0.5039 0.00829 0.00174 -0.1549 0.5386 0.1458
-1.000 0.5323 0.00836 0.00175 -0.1549 0.5240 0.1488
-0.750 0.5606 0.00843 0.00176 -0.1549 0.5080 0.1537
-0.500 0.5889 0.00851 0.00179 -0.1549 0.4923 0.1587
-0.250 0.6169 0.00860 0.00182 -0.1549 0.4768 0.1657
0.000 0.6447 0.00870 0.00187 -0.1549 0.4589 0.1753
0.250 0.6722 0.00883 0.00195 -0.1548 0.4394 0.1900
0.500 0.7004 0.00885 0.00202 -0.1549 0.4269 0.2254
0.750 0.7286 0.00890 0.00210 -0.1550 0.4183 0.2564
1.000 0.7573 0.00892 0.00217 -0.1551 0.4129 0.2772
1.250 0.7856 0.00899 0.00224 -0.1551 0.4072 0.2913
1.500 0.8138 0.00906 0.00232 -0.1551 0.4018 0.3032
1.750 0.8423 0.00910 0.00239 -0.1551 0.3969 0.3141
2.000 0.8703 0.00918 0.00248 -0.1551 0.3901 0.3253
2.250 0.8983 0.00927 0.00257 -0.1551 0.3830 0.3398
2.500 0.9262 0.00934 0.00268 -0.1551 0.3741 0.3598
2.750 0.9541 0.00941 0.00279 -0.1550 0.3665 0.3852
3.000 0.9817 0.00950 0.00292 -0.1550 0.3560 0.4177
3.250 1.0089 0.00963 0.00307 -0.1549 0.3419 0.4480
3.500 1.0287 0.01042 0.00349 -0.1536 0.2619 0.4695
3.750 1.0516 0.01095 0.00386 -0.1528 0.2266 0.4860
4.000 1.0772 0.01121 0.00410 -0.1523 0.2144 0.5021
4.250 1.1037 0.01139 0.00429 -0.1521 0.2078 0.5177
4.500 1.1292 0.01164 0.00453 -0.1517 0.1989 0.5311
4.750 1.1558 0.01179 0.00472 -0.1514 0.1942 0.5492
5.000 1.1820 0.01195 0.00493 -0.1511 0.1895 0.5717
5.250 1.2078 0.01215 0.00516 -0.1507 0.1846 0.5938
5.500 1.2337 0.01233 0.00540 -0.1503 0.1803 0.6208
5.750 1.2595 0.01251 0.00562 -0.1499 0.1753 0.6451
6.000 1.2837 0.01281 0.00589 -0.1493 0.1656 0.6628
6.250 1.3080 0.01309 0.00616 -0.1487 0.1543 0.6778
6.500 1.3310 0.01345 0.00646 -0.1479 0.1399 0.6904
6.750 1.3512 0.01400 0.00690 -0.1467 0.1147 0.7034
7.000 1.3696 0.01465 0.00743 -0.1451 0.0924 0.7196
7.250 1.3910 0.01503 0.00784 -0.1441 0.0850 0.7441
7.500 1.4082 0.01495 0.00817 -0.1420 0.0821 1.0000
7.750 1.4298 0.01532 0.00854 -0.1409 0.0797 1.0000
8.000 1.4504 0.01572 0.00892 -0.1397 0.0767 1.0000
8.250 1.4700 0.01608 0.00929 -0.1382 0.0741 1.0000
8.500 1.4896 0.01641 0.00965 -0.1368 0.0727 1.0000
8.750 1.5086 0.01680 0.01005 -0.1353 0.0707 1.0000
9.000 1.5261 0.01727 0.01052 -0.1337 0.0676 1.0000
9.250 1.5421 0.01784 0.01107 -0.1318 0.0631 1.0000
9.500 1.5594 0.01833 0.01157 -0.1302 0.0582 1.0000
9.750 1.5567 0.02004 0.01304 -0.1259 0.0262 1.0000
10.000 1.5660 0.02110 0.01408 -0.1234 0.0189 1.0000
10.250 1.5789 0.02195 0.01494 -0.1214 0.0165 1.0000
10.500 1.5921 0.02281 0.01582 -0.1196 0.0150 1.0000
10.750 1.6052 0.02368 0.01673 -0.1179 0.0140 1.0000
11.000 1.6175 0.02464 0.01771 -0.1161 0.0131 1.0000
11.250 1.6289 0.02569 0.01879 -0.1143 0.0123 1.0000
11.500 1.6413 0.02668 0.01982 -0.1126 0.0118 1.0000
11.750 1.6529 0.02775 0.02094 -0.1110 0.0114 1.0000
12.000 1.6637 0.02891 0.02214 -0.1093 0.0109 1.0000
12.250 1.6736 0.03017 0.02344 -0.1077 0.0104 1.0000
12.500 1.6822 0.03156 0.02487 -0.1060 0.0100 1.0000
12.750 1.6897 0.03307 0.02643 -0.1043 0.0096 1.0000
13.000 1.6981 0.03455 0.02797 -0.1028 0.0094 1.0000
13.250 1.7062 0.03608 0.02955 -0.1014 0.0092 1.0000
13.500 1.7134 0.03772 0.03126 -0.1000 0.0090 1.0000
13.750 1.7199 0.03948 0.03307 -0.0987 0.0087 1.0000
14.000 1.7257 0.04135 0.03501 -0.0974 0.0085 1.0000
14.250 1.7309 0.04335 0.03707 -0.0962 0.0083 1.0000
14.500 1.7351 0.04549 0.03927 -0.0951 0.0081 1.0000
14.750 1.7386 0.04778 0.04162 -0.0941 0.0079 1.0000
15.000 1.7411 0.05025 0.04415 -0.0932 0.0077 1.0000
15.250 1.7425 0.05291 0.04689 -0.0924 0.0075 1.0000
15.500 1.7417 0.05587 0.04993 -0.0917 0.0073 1.0000
15.750 1.7437 0.05856 0.05269 -0.0912 0.0072 1.0000
16.000 1.7448 0.06141 0.05562 -0.0907 0.0071 1.0000
16.250 1.7452 0.06441 0.05870 -0.0903 0.0069 1.0000
16.500 1.7444 0.06760 0.06197 -0.0901 0.0068 1.0000
16.750 1.7425 0.07094 0.06540 -0.0899 0.0067 1.0000
17.000 1.7397 0.07446 0.06900 -0.0899 0.0066 1.0000
17.250 1.7361 0.07815 0.07278 -0.0899 0.0065 1.0000
17.500 1.7319 0.08198 0.07669 -0.0901 0.0064 1.0000
17.750 1.7270 0.08594 0.08075 -0.0905 0.0064 1.0000
18.000 1.7211 0.09006 0.08497 -0.0909 0.0063 1.0000
18.250 1.7149 0.09432 0.08931 -0.0915 0.0062 1.0000
18.500 1.7080 0.09873 0.09381 -0.0922 0.0061 1.0000
18.750 1.7003 0.10330 0.09847 -0.0932 0.0060 1.0000
19.000 1.6921 0.10798 0.10325 -0.0942 0.0060 1.0000
19.250 1.6833 0.11278 0.10815 -0.0954 0.0059 1.0000
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