GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 435 AIRFOIL (goe435-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.18 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe435-il-1000000.txt Download as CSV file: xf-goe435-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 435 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7275 0.09459 0.09071 -0.0689 0.9293 0.0622
-17.500 -0.7233 0.09240 0.08842 -0.0691 0.9022 0.0623
-17.250 -0.7190 0.09013 0.08600 -0.0696 0.8728 0.0624
-17.000 -0.7152 0.08757 0.08329 -0.0705 0.8477 0.0625
-16.750 -0.7104 0.08500 0.08060 -0.0716 0.8282 0.0626
-16.500 -0.7054 0.08244 0.07794 -0.0728 0.8130 0.0627
-16.250 -0.7024 0.07958 0.07498 -0.0742 0.8003 0.0628
-16.000 -0.6975 0.07699 0.07231 -0.0754 0.7902 0.0628
-15.750 -0.6946 0.07416 0.06941 -0.0767 0.7812 0.0630
-15.500 -0.6952 0.07100 0.06615 -0.0782 0.7720 0.0632
-15.250 -0.6966 0.06775 0.06284 -0.0798 0.7662 0.0635
-15.000 -0.6990 0.06432 0.05935 -0.0814 0.7615 0.0637
-14.750 -0.7020 0.06090 0.05586 -0.0831 0.7565 0.0639
-14.500 -0.7036 0.05769 0.05257 -0.0846 0.7511 0.0642
-14.250 -0.7063 0.05437 0.04915 -0.0863 0.7445 0.0644
-14.000 -0.7058 0.05145 0.04619 -0.0877 0.7410 0.0646
-13.750 -0.7074 0.04830 0.04299 -0.0894 0.7376 0.0648
-13.500 -0.7057 0.04561 0.04025 -0.0907 0.7339 0.0651
-13.250 -0.7062 0.04272 0.03728 -0.0922 0.7301 0.0653
-13.000 -0.7040 0.04023 0.03473 -0.0935 0.7261 0.0656
-12.750 -0.7026 0.03764 0.03206 -0.0948 0.7217 0.0658
-12.500 -0.6990 0.03523 0.02958 -0.0962 0.7170 0.0660
-12.250 -0.6936 0.03293 0.02724 -0.0975 0.7151 0.0663
-12.000 -0.6870 0.03066 0.02493 -0.0989 0.7128 0.0666
-11.750 -0.6787 0.02852 0.02275 -0.1003 0.7100 0.0669
-11.500 -0.6684 0.02652 0.02070 -0.1018 0.7068 0.0672
-11.250 -0.6560 0.02468 0.01879 -0.1033 0.7033 0.0676
-11.000 -0.6427 0.02298 0.01703 -0.1047 0.6996 0.0679
-10.750 -0.6295 0.02145 0.01542 -0.1061 0.6951 0.0683
-10.500 -0.6085 0.02012 0.01403 -0.1082 0.6907 0.0686
-10.250 -0.5842 0.01895 0.01283 -0.1105 0.6887 0.0690
-10.000 -0.5580 0.01784 0.01167 -0.1129 0.6858 0.0695
-9.750 -0.5310 0.01681 0.01060 -0.1152 0.6823 0.0707
-9.500 -0.5042 0.01612 0.00987 -0.1164 0.6782 0.0718
-9.250 -0.4769 0.01556 0.00928 -0.1173 0.6737 0.0729
-9.000 -0.4492 0.01512 0.00879 -0.1181 0.6685 0.0741
-8.750 -0.4206 0.01472 0.00836 -0.1189 0.6646 0.0753
-8.500 -0.3918 0.01426 0.00790 -0.1196 0.6612 0.0774
-8.250 -0.3635 0.01372 0.00737 -0.1204 0.6566 0.0811
-8.000 -0.3386 0.01245 0.00634 -0.1219 0.6513 0.1304
-7.750 -0.3086 0.01236 0.00628 -0.1223 0.6450 0.1397
-7.500 -0.2777 0.01232 0.00625 -0.1227 0.6398 0.1441
-7.250 -0.2468 0.01226 0.00618 -0.1231 0.6333 0.1468
-7.000 -0.2167 0.01216 0.00607 -0.1235 0.6251 0.1494
-6.750 -0.1862 0.01212 0.00603 -0.1239 0.6170 0.1514
-6.500 -0.1558 0.01210 0.00598 -0.1242 0.6062 0.1530
-6.250 -0.1257 0.01210 0.00592 -0.1246 0.5945 0.1544
-5.750 -0.0659 0.01215 0.00585 -0.1251 0.5682 0.1561
-5.500 -0.0362 0.01223 0.00585 -0.1253 0.5574 0.1566
-5.250 -0.0069 0.01200 0.00558 -0.1258 0.5491 0.1584
-5.000 0.0222 0.01191 0.00544 -0.1261 0.5402 0.1599
-4.750 0.0523 0.01183 0.00535 -0.1265 0.5345 0.1611
-4.500 0.0823 0.01178 0.00528 -0.1269 0.5288 0.1621
-4.250 0.1119 0.01176 0.00522 -0.1272 0.5228 0.1630
-4.000 0.1415 0.01175 0.00517 -0.1275 0.5168 0.1638
-3.750 0.1722 0.01168 0.00510 -0.1279 0.5138 0.1646
-3.500 0.2025 0.01162 0.00504 -0.1283 0.5104 0.1653
-3.250 0.2326 0.01159 0.00499 -0.1287 0.5066 0.1661
-3.000 0.2624 0.01159 0.00495 -0.1290 0.5023 0.1670
-2.750 0.2917 0.01161 0.00493 -0.1292 0.4971 0.1676
-2.500 0.3219 0.01159 0.00490 -0.1296 0.4941 0.1682
-2.250 0.3525 0.01155 0.00487 -0.1300 0.4923 0.1687
-2.000 0.3831 0.01152 0.00484 -0.1304 0.4902 0.1691
-1.750 0.4134 0.01149 0.00482 -0.1308 0.4876 0.1693
-1.500 0.4435 0.01138 0.00469 -0.1312 0.4847 0.1704
-1.250 0.4734 0.01132 0.00460 -0.1316 0.4817 0.1717
-1.000 0.5030 0.01128 0.00455 -0.1320 0.4785 0.1734
-0.750 0.5322 0.01130 0.00454 -0.1322 0.4746 0.1750
-0.500 0.5622 0.01128 0.00453 -0.1326 0.4721 0.1761
-0.250 0.5928 0.01122 0.00449 -0.1330 0.4703 0.1773
0.000 0.6232 0.01118 0.00447 -0.1334 0.4681 0.1786
0.250 0.6534 0.01115 0.00446 -0.1338 0.4656 0.1797
0.500 0.6832 0.01115 0.00446 -0.1341 0.4627 0.1807
0.750 0.7125 0.01118 0.00446 -0.1343 0.4592 0.1816
1.000 0.7411 0.01124 0.00449 -0.1344 0.4553 0.1824
1.250 0.7694 0.01133 0.00456 -0.1345 0.4511 0.1832
1.500 0.7996 0.01130 0.00455 -0.1348 0.4493 0.1844
1.750 0.8297 0.01125 0.00454 -0.1352 0.4465 0.1875
2.000 0.8593 0.01123 0.00455 -0.1355 0.4427 0.1913
2.250 0.8879 0.01125 0.00457 -0.1356 0.4385 0.1952
2.500 0.9155 0.01132 0.00463 -0.1356 0.4338 0.2014
2.750 0.9446 0.01117 0.00463 -0.1361 0.4297 0.2424
3.000 0.9753 0.01088 0.00468 -0.1369 0.4256 0.3479
3.250 1.0033 0.01097 0.00480 -0.1369 0.4199 0.3621
3.500 1.0291 0.01113 0.00494 -0.1366 0.4131 0.3701
3.750 1.0569 0.01123 0.00507 -0.1365 0.4074 0.3771
4.000 1.0826 0.01140 0.00521 -0.1362 0.3988 0.3816
4.250 1.1069 0.01163 0.00538 -0.1356 0.3888 0.3842
4.500 1.1280 0.01189 0.00559 -0.1345 0.3750 0.3898
4.750 1.1444 0.01222 0.00586 -0.1326 0.3601 0.3937
5.000 1.1615 0.01261 0.00619 -0.1309 0.3463 0.3968
5.250 1.1806 0.01305 0.00657 -0.1296 0.3346 0.3996
5.500 1.1982 0.01357 0.00703 -0.1282 0.3239 0.4020
5.750 1.2188 0.01398 0.00741 -0.1272 0.3162 0.4040
6.000 1.2357 0.01455 0.00793 -0.1258 0.3080 0.4055
6.250 1.2572 0.01493 0.00830 -0.1251 0.3030 0.4076
6.500 1.2766 0.01540 0.00878 -0.1242 0.2976 0.4116
6.750 1.2937 0.01601 0.00936 -0.1230 0.2916 0.4151
7.000 1.3138 0.01648 0.00986 -0.1222 0.2875 0.4185
7.250 1.3337 0.01698 0.01037 -0.1214 0.2834 0.4221
7.500 1.3512 0.01763 0.01101 -0.1204 0.2791 0.4250
7.750 1.3664 0.01841 0.01178 -0.1192 0.2743 0.4271
8.000 1.3853 0.01903 0.01241 -0.1185 0.2713 0.4288
8.250 1.4050 0.01961 0.01301 -0.1179 0.2687 0.4301
8.500 1.4236 0.02027 0.01369 -0.1172 0.2656 0.4339
8.750 1.4395 0.02111 0.01455 -0.1164 0.2623 0.4381
9.000 1.4538 0.02208 0.01553 -0.1154 0.2585 0.4418
9.250 1.4682 0.02307 0.01655 -0.1145 0.2553 0.4453
9.500 1.4876 0.02375 0.01726 -0.1141 0.2533 0.4490
9.750 1.5040 0.02463 0.01818 -0.1134 0.2508 0.4526
10.000 1.5189 0.02562 0.01918 -0.1127 0.2479 0.4554
10.250 1.5312 0.02682 0.02041 -0.1118 0.2445 0.4622
10.500 1.5405 0.02825 0.02186 -0.1108 0.2406 0.4692
10.750 1.5563 0.02922 0.02289 -0.1102 0.2384 0.4770
11.000 1.5712 0.03029 0.02401 -0.1096 0.2363 0.4869
11.250 1.5857 0.03138 0.02518 -0.1090 0.2339 0.5020
11.500 1.5975 0.03271 0.02658 -0.1084 0.2312 0.5238
11.750 1.6069 0.03426 0.02822 -0.1076 0.2284 0.5562
12.000 1.6147 0.03593 0.02997 -0.1068 0.2252 0.5933
12.250 1.6271 0.03727 0.03146 -0.1063 0.2234 0.6337
12.750 1.6534 0.03980 0.03420 -0.1052 0.2194 0.6965
13.000 1.6611 0.04157 0.03604 -0.1045 0.2171 0.7191
13.250 1.6683 0.04336 0.03788 -0.1037 0.2146 0.7376
13.500 1.6716 0.04554 0.04011 -0.1028 0.2118 0.7516
13.750 1.6782 0.04745 0.04206 -0.1021 0.2096 0.7647
14.000 1.6906 0.04883 0.04352 -0.1016 0.2080 0.7783
14.250 1.6984 0.05069 0.04545 -0.1011 0.2061 0.7902
14.750 1.7105 0.05471 0.04958 -0.0999 0.2016 0.8169
15.000 1.7119 0.05722 0.05216 -0.0993 0.1990 0.8351
15.250 1.7093 0.05952 0.05472 -0.0979 0.1965 0.9747
15.500 1.7187 0.06133 0.05657 -0.0977 0.1952 1.0000
15.750 1.7274 0.06317 0.05844 -0.0974 0.1934 1.0000
16.000 1.7314 0.06552 0.06083 -0.0970 0.1915 1.0000
16.250 1.7356 0.06784 0.06318 -0.0966 0.1895 1.0000
16.500 1.7362 0.07056 0.06592 -0.0963 0.1874 1.0000
16.750 1.7351 0.07350 0.06887 -0.0960 0.1851 1.0000
17.000 1.7390 0.07585 0.07125 -0.0957 0.1832 1.0000
17.250 1.7440 0.07815 0.07361 -0.0956 0.1817 1.0000
17.500 1.7497 0.08034 0.07583 -0.0954 0.1799 1.0000
17.750 1.7543 0.08264 0.07816 -0.0953 0.1779 1.0000
18.000 1.7527 0.08568 0.08123 -0.0952 0.1757 1.0000
18.250 1.7518 0.08863 0.08419 -0.0951 0.1734 1.0000
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