GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 501 AIRFOIL (goe501-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.89 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe501-il-1000000.txt Download as CSV file: xf-goe501-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 501 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6448 0.06407 0.06176 -0.1062 0.9895 0.0248
-14.250 -0.6779 0.05272 0.05022 -0.1192 0.9854 0.0249
-14.000 -0.6922 0.04299 0.04030 -0.1332 0.9820 0.0251
-13.750 -0.6983 0.03448 0.03161 -0.1469 0.9743 0.0253
-13.500 -0.6769 0.02708 0.02395 -0.1623 0.9696 0.0257
-13.250 -0.6647 0.02236 0.01901 -0.1701 0.9606 0.0264
-13.000 -0.6404 0.02126 0.01785 -0.1717 0.9566 0.0271
-12.750 -0.6195 0.02049 0.01702 -0.1719 0.9516 0.0277
-12.500 -0.5973 0.01978 0.01623 -0.1721 0.9465 0.0283
-12.250 -0.5740 0.01904 0.01539 -0.1724 0.9421 0.0289
-12.000 -0.5513 0.01838 0.01463 -0.1724 0.9372 0.0294
-11.750 -0.5276 0.01787 0.01401 -0.1723 0.9320 0.0298
-11.500 -0.5067 0.01670 0.01273 -0.1724 0.9269 0.0307
-11.250 -0.4816 0.01626 0.01227 -0.1724 0.9223 0.0315
-11.000 -0.4564 0.01587 0.01184 -0.1723 0.9167 0.0321
-10.750 -0.4305 0.01546 0.01136 -0.1722 0.9115 0.0328
-10.500 -0.4045 0.01503 0.01085 -0.1722 0.9062 0.0335
-10.250 -0.3784 0.01469 0.01043 -0.1721 0.8996 0.0342
-10.000 -0.3511 0.01443 0.01007 -0.1721 0.8937 0.0346
-9.750 -0.3274 0.01349 0.00905 -0.1720 0.8856 0.0358
-9.500 -0.3008 0.01315 0.00864 -0.1720 0.8777 0.0365
-9.250 -0.2738 0.01293 0.00838 -0.1719 0.8685 0.0373
-9.000 -0.2468 0.01267 0.00803 -0.1717 0.8593 0.0381
-8.750 -0.2199 0.01239 0.00767 -0.1716 0.8496 0.0389
-8.500 -0.1927 0.01216 0.00733 -0.1715 0.8410 0.0396
-8.250 -0.1657 0.01184 0.00692 -0.1714 0.8327 0.0403
-8.000 -0.1394 0.01130 0.00631 -0.1714 0.8252 0.0415
-7.750 -0.1119 0.01108 0.00605 -0.1714 0.8176 0.0424
-7.500 -0.0843 0.01090 0.00580 -0.1713 0.8109 0.0433
-7.250 -0.0563 0.01073 0.00558 -0.1713 0.8046 0.0443
-7.000 -0.0285 0.01058 0.00536 -0.1712 0.7988 0.0453
-6.750 -0.0004 0.01044 0.00515 -0.1712 0.7935 0.0460
-6.500 0.0270 0.00997 0.00463 -0.1712 0.7878 0.0474
-6.250 0.0547 0.00976 0.00438 -0.1712 0.7822 0.0486
-6.000 0.0830 0.00964 0.00422 -0.1712 0.7778 0.0498
-5.750 0.1114 0.00951 0.00407 -0.1712 0.7734 0.0512
-5.500 0.1397 0.00939 0.00390 -0.1712 0.7683 0.0524
-5.250 0.1678 0.00933 0.00377 -0.1711 0.7634 0.0532
-5.000 0.1959 0.00894 0.00336 -0.1712 0.7594 0.0553
-4.750 0.2244 0.00879 0.00321 -0.1713 0.7554 0.0569
-4.500 0.2528 0.00869 0.00309 -0.1713 0.7511 0.0587
-4.250 0.2811 0.00863 0.00298 -0.1712 0.7468 0.0603
-4.000 0.3097 0.00857 0.00289 -0.1713 0.7433 0.0614
-3.750 0.3382 0.00830 0.00260 -0.1713 0.7395 0.0640
-3.500 0.3666 0.00817 0.00246 -0.1714 0.7351 0.0663
-3.250 0.3947 0.00811 0.00235 -0.1713 0.7299 0.0686
-3.000 0.4231 0.00804 0.00226 -0.1713 0.7251 0.0705
-2.750 0.4513 0.00791 0.00211 -0.1712 0.7190 0.0730
-2.500 0.4791 0.00781 0.00197 -0.1711 0.7128 0.0770
-2.250 0.5075 0.00771 0.00188 -0.1711 0.7076 0.0807
-2.000 0.5358 0.00762 0.00178 -0.1711 0.7020 0.0863
-1.750 0.5636 0.00749 0.00170 -0.1710 0.6964 0.1045
-1.500 0.5918 0.00734 0.00169 -0.1710 0.6907 0.1488
-1.250 0.6198 0.00729 0.00167 -0.1709 0.6836 0.1641
-1.000 0.6474 0.00727 0.00165 -0.1708 0.6762 0.1760
-0.750 0.6752 0.00724 0.00163 -0.1707 0.6671 0.1867
-0.250 0.7292 0.00720 0.00163 -0.1701 0.6430 0.2271
0.000 0.7553 0.00722 0.00166 -0.1697 0.6231 0.2547
0.250 0.7793 0.00735 0.00172 -0.1689 0.5925 0.2803
0.500 0.8024 0.00758 0.00183 -0.1679 0.5620 0.3019
0.750 0.8266 0.00778 0.00195 -0.1671 0.5398 0.3222
1.000 0.8518 0.00793 0.00207 -0.1665 0.5253 0.3377
1.250 0.8770 0.00808 0.00218 -0.1660 0.5138 0.3510
1.500 0.9033 0.00818 0.00228 -0.1656 0.5043 0.3652
1.750 0.9289 0.00831 0.00239 -0.1651 0.4955 0.3786
2.000 0.9551 0.00840 0.00249 -0.1647 0.4873 0.3915
2.250 0.9805 0.00852 0.00261 -0.1642 0.4796 0.4079
2.500 1.0070 0.00857 0.00271 -0.1639 0.4732 0.4273
2.750 1.0324 0.00868 0.00283 -0.1634 0.4661 0.4467
3.000 1.0583 0.00873 0.00295 -0.1630 0.4601 0.4766
3.250 1.0840 0.00877 0.00310 -0.1626 0.4537 0.5300
3.500 1.1084 0.00886 0.00328 -0.1619 0.4468 0.5859
3.750 1.1342 0.00887 0.00341 -0.1615 0.4411 0.6393
4.000 1.1581 0.00887 0.00358 -0.1608 0.4338 0.7178
4.250 1.1818 0.00858 0.00374 -0.1598 0.4266 1.0000
4.500 1.2065 0.00875 0.00387 -0.1592 0.4187 1.0000
4.750 1.2303 0.00894 0.00402 -0.1584 0.4096 1.0000
5.000 1.2539 0.00913 0.00418 -0.1576 0.4003 1.0000
5.250 1.2774 0.00932 0.00433 -0.1568 0.3917 1.0000
5.500 1.2994 0.00957 0.00452 -0.1557 0.3813 1.0000
5.750 1.3216 0.00977 0.00469 -0.1546 0.3703 1.0000
6.000 1.3414 0.01002 0.00489 -0.1531 0.3584 1.0000
6.250 1.3598 0.01032 0.00513 -0.1513 0.3439 1.0000
6.500 1.3768 0.01069 0.00540 -0.1493 0.3251 1.0000
6.750 1.3904 0.01121 0.00578 -0.1467 0.2988 1.0000
7.000 1.3968 0.01208 0.00638 -0.1431 0.2520 1.0000
7.250 1.3964 0.01333 0.00727 -0.1384 0.1946 1.0000
7.500 1.4109 0.01389 0.00776 -0.1363 0.1824 1.0000
7.750 1.4283 0.01432 0.00818 -0.1346 0.1766 1.0000
8.000 1.4457 0.01475 0.00860 -0.1329 0.1726 1.0000
8.250 1.4624 0.01523 0.00907 -0.1312 0.1681 1.0000
8.500 1.4795 0.01569 0.00954 -0.1296 0.1643 1.0000
8.750 1.4982 0.01606 0.00995 -0.1283 0.1618 1.0000
9.000 1.5156 0.01652 0.01042 -0.1268 0.1584 1.0000
9.250 1.5310 0.01709 0.01098 -0.1250 0.1543 1.0000
9.500 1.5453 0.01772 0.01161 -0.1232 0.1494 1.0000
9.750 1.5649 0.01808 0.01201 -0.1221 0.1469 1.0000
10.000 1.5819 0.01858 0.01254 -0.1207 0.1429 1.0000
10.250 1.5960 0.01927 0.01321 -0.1189 0.1368 1.0000
10.500 1.6123 0.01983 0.01379 -0.1175 0.1317 1.0000
10.750 1.6252 0.02062 0.01453 -0.1157 0.1202 1.0000
11.000 1.6278 0.02207 0.01577 -0.1128 0.0917 1.0000
11.250 1.6298 0.02362 0.01724 -0.1100 0.0778 1.0000
11.500 1.6377 0.02484 0.01845 -0.1079 0.0717 1.0000
11.750 1.6456 0.02609 0.01972 -0.1059 0.0676 1.0000
12.000 1.6547 0.02731 0.02096 -0.1042 0.0641 1.0000
12.250 1.6650 0.02846 0.02215 -0.1026 0.0618 1.0000
12.500 1.6732 0.02982 0.02353 -0.1010 0.0592 1.0000
12.750 1.6798 0.03135 0.02508 -0.0993 0.0561 1.0000
13.000 1.6902 0.03260 0.02639 -0.0980 0.0546 1.0000
13.250 1.6997 0.03396 0.02781 -0.0967 0.0527 1.0000
13.500 1.7071 0.03555 0.02942 -0.0954 0.0505 1.0000
13.750 1.7125 0.03737 0.03126 -0.0940 0.0481 1.0000
14.000 1.7214 0.03890 0.03285 -0.0929 0.0464 1.0000
14.250 1.7293 0.04056 0.03455 -0.0919 0.0443 1.0000
14.500 1.7329 0.04268 0.03669 -0.0907 0.0413 1.0000
14.750 1.7395 0.04456 0.03862 -0.0898 0.0388 1.0000
15.000 1.7420 0.04691 0.04096 -0.0888 0.0348 1.0000
15.250 1.7445 0.04931 0.04339 -0.0879 0.0308 1.0000
15.500 1.7440 0.05214 0.04624 -0.0871 0.0267 1.0000
15.750 1.7424 0.05519 0.04931 -0.0864 0.0234 1.0000
16.000 1.7392 0.05851 0.05266 -0.0858 0.0208 1.0000
16.250 1.7391 0.06158 0.05579 -0.0855 0.0195 1.0000
16.500 1.7364 0.06507 0.05934 -0.0853 0.0182 1.0000
16.750 1.7332 0.06874 0.06308 -0.0853 0.0173 1.0000
17.000 1.7329 0.07209 0.06652 -0.0854 0.0166 1.0000
17.250 1.7311 0.07573 0.07023 -0.0857 0.0161 1.0000
17.500 1.7280 0.07963 0.07422 -0.0861 0.0155 1.0000
17.750 1.7225 0.08396 0.07862 -0.0867 0.0149 1.0000
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Polar data table (+)
Polar graphs
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