GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 435 AIRFOIL (goe435-il) Reynolds number: 500,000 Max Cl/Cd: 69.9 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe435-il-500000-n5.txt Download as CSV file: xf-goe435-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6044 0.09221 0.08672 -0.0693 0.7820 0.0621
-16.000 -0.6005 0.08936 0.08378 -0.0707 0.7742 0.0623
-15.750 -0.5976 0.08638 0.08072 -0.0721 0.7679 0.0625
-15.500 -0.5947 0.08336 0.07764 -0.0736 0.7623 0.0627
-15.250 -0.5931 0.08022 0.07443 -0.0751 0.7563 0.0628
-15.000 -0.5923 0.07703 0.07116 -0.0766 0.7502 0.0630
-14.500 -0.5973 0.06990 0.06389 -0.0801 0.7412 0.0635
-14.250 -0.6000 0.06632 0.06026 -0.0819 0.7377 0.0638
-14.000 -0.6025 0.06283 0.05671 -0.0836 0.7337 0.0640
-13.750 -0.6054 0.05935 0.05315 -0.0853 0.7292 0.0643
-13.500 -0.6059 0.05621 0.04994 -0.0869 0.7246 0.0646
-13.250 -0.6066 0.05311 0.04675 -0.0885 0.7205 0.0648
-13.000 -0.6058 0.05022 0.04379 -0.0900 0.7168 0.0651
-12.750 -0.6044 0.04743 0.04095 -0.0914 0.7140 0.0655
-12.500 -0.6026 0.04473 0.03820 -0.0929 0.7108 0.0658
-12.250 -0.5997 0.04228 0.03569 -0.0941 0.7071 0.0662
-12.000 -0.5966 0.03982 0.03317 -0.0954 0.7032 0.0666
-11.750 -0.5914 0.03760 0.03088 -0.0966 0.6993 0.0670
-11.500 -0.5857 0.03537 0.02858 -0.0978 0.6955 0.0674
-11.250 -0.5784 0.03328 0.02641 -0.0991 0.6917 0.0678
-11.000 -0.5695 0.03128 0.02437 -0.1004 0.6889 0.0682
-10.750 -0.5589 0.02938 0.02243 -0.1017 0.6857 0.0686
-10.500 -0.5468 0.02759 0.02059 -0.1030 0.6820 0.0690
-10.250 -0.5352 0.02575 0.01870 -0.1045 0.6780 0.0696
-10.000 -0.5260 0.02399 0.01688 -0.1056 0.6739 0.0703
-9.750 -0.5104 0.02244 0.01525 -0.1074 0.6697 0.0711
-9.500 -0.4899 0.02110 0.01384 -0.1096 0.6656 0.0721
-9.250 -0.4658 0.01996 0.01267 -0.1118 0.6618 0.0734
-9.000 -0.4398 0.01905 0.01172 -0.1137 0.6572 0.0748
-8.750 -0.4137 0.01831 0.01093 -0.1151 0.6519 0.0769
-8.500 -0.3883 0.01759 0.01015 -0.1161 0.6463 0.0807
-8.250 -0.3660 0.01628 0.00897 -0.1177 0.6410 0.1041
-8.000 -0.3372 0.01596 0.00879 -0.1185 0.6347 0.1353
-7.750 -0.3079 0.01578 0.00860 -0.1189 0.6276 0.1400
-7.500 -0.2789 0.01566 0.00842 -0.1193 0.6208 0.1435
-7.250 -0.2492 0.01552 0.00824 -0.1197 0.6134 0.1453
-7.000 -0.2203 0.01533 0.00802 -0.1201 0.6044 0.1471
-6.750 -0.1912 0.01518 0.00785 -0.1205 0.5958 0.1489
-6.500 -0.1620 0.01506 0.00769 -0.1209 0.5856 0.1507
-6.250 -0.1331 0.01498 0.00754 -0.1212 0.5762 0.1523
-6.000 -0.1040 0.01490 0.00740 -0.1215 0.5665 0.1537
-5.750 -0.0752 0.01484 0.00727 -0.1217 0.5582 0.1549
-5.500 -0.0458 0.01479 0.00716 -0.1220 0.5507 0.1559
-5.250 -0.0169 0.01475 0.00705 -0.1222 0.5433 0.1565
-5.000 0.0117 0.01462 0.00688 -0.1225 0.5371 0.1574
-4.750 0.0410 0.01446 0.00671 -0.1229 0.5318 0.1584
-4.500 0.0701 0.01434 0.00657 -0.1233 0.5270 0.1594
-4.250 0.0992 0.01426 0.00646 -0.1236 0.5224 0.1603
-3.750 0.1577 0.01412 0.00628 -0.1242 0.5136 0.1624
-3.500 0.1872 0.01407 0.00621 -0.1246 0.5090 0.1637
-3.250 0.2164 0.01403 0.00615 -0.1248 0.5041 0.1647
-3.000 0.2452 0.01401 0.00608 -0.1250 0.4994 0.1655
-2.500 0.3039 0.01393 0.00596 -0.1256 0.4922 0.1668
-2.250 0.3335 0.01388 0.00591 -0.1259 0.4884 0.1675
-2.000 0.3629 0.01386 0.00587 -0.1262 0.4846 0.1683
-1.750 0.3921 0.01387 0.00585 -0.1264 0.4811 0.1691
-1.500 0.4210 0.01384 0.00580 -0.1267 0.4778 0.1702
-1.250 0.4497 0.01380 0.00574 -0.1269 0.4744 0.1716
-1.000 0.4791 0.01375 0.00570 -0.1272 0.4719 0.1730
-0.750 0.5089 0.01369 0.00566 -0.1276 0.4696 0.1743
-0.500 0.5385 0.01364 0.00564 -0.1279 0.4667 0.1752
-0.250 0.5677 0.01362 0.00562 -0.1282 0.4633 0.1762
0.000 0.5966 0.01362 0.00562 -0.1284 0.4600 0.1772
0.250 0.6252 0.01365 0.00563 -0.1285 0.4568 0.1784
0.500 0.6532 0.01369 0.00565 -0.1285 0.4533 0.1797
0.750 0.6816 0.01373 0.00569 -0.1287 0.4501 0.1809
1.000 0.7107 0.01373 0.00571 -0.1289 0.4469 0.1821
1.250 0.7393 0.01375 0.00574 -0.1290 0.4433 0.1833
1.750 0.7945 0.01383 0.00583 -0.1290 0.4348 0.1882
2.000 0.8210 0.01391 0.00589 -0.1288 0.4304 0.1915
2.250 0.8492 0.01392 0.00595 -0.1289 0.4261 0.1956
2.750 0.9026 0.01394 0.00607 -0.1288 0.4151 0.2266
3.000 0.9300 0.01374 0.00622 -0.1292 0.4094 0.3366
3.250 0.9554 0.01387 0.00638 -0.1289 0.4018 0.3492
3.500 0.9763 0.01410 0.00658 -0.1277 0.3937 0.3582
3.750 0.9982 0.01428 0.00675 -0.1267 0.3851 0.3638
4.000 1.0162 0.01457 0.00702 -0.1252 0.3754 0.3689
4.250 1.0362 0.01491 0.00734 -0.1241 0.3641 0.3740
4.500 1.0550 0.01537 0.00774 -0.1229 0.3529 0.3787
4.750 1.0720 0.01593 0.00822 -0.1215 0.3417 0.3826
5.000 1.0912 0.01641 0.00867 -0.1204 0.3325 0.3855
5.250 1.1079 0.01700 0.00924 -0.1192 0.3243 0.3890
5.500 1.1272 0.01751 0.00975 -0.1183 0.3173 0.3927
5.750 1.1436 0.01817 0.01039 -0.1170 0.3102 0.3961
6.000 1.1611 0.01880 0.01101 -0.1160 0.3043 0.3994
6.250 1.1787 0.01945 0.01165 -0.1151 0.2985 0.4025
6.500 1.1937 0.02027 0.01243 -0.1139 0.2926 0.4047
6.750 1.2100 0.02104 0.01320 -0.1129 0.2876 0.4067
7.000 1.2279 0.02174 0.01392 -0.1122 0.2826 0.4100
7.250 1.2430 0.02263 0.01483 -0.1113 0.2777 0.4135
7.500 1.2568 0.02363 0.01582 -0.1103 0.2734 0.4166
7.750 1.2742 0.02442 0.01665 -0.1097 0.2704 0.4193
8.000 1.2918 0.02522 0.01748 -0.1090 0.2673 0.4220
8.250 1.3074 0.02616 0.01844 -0.1083 0.2641 0.4245
8.500 1.3216 0.02721 0.01951 -0.1075 0.2608 0.4271
8.750 1.3336 0.02843 0.02073 -0.1066 0.2575 0.4294
9.000 1.3478 0.02953 0.02185 -0.1059 0.2546 0.4326
9.250 1.3639 0.03047 0.02284 -0.1053 0.2517 0.4367
9.500 1.3774 0.03164 0.02406 -0.1047 0.2485 0.4404
9.750 1.3896 0.03291 0.02536 -0.1039 0.2452 0.4440
10.000 1.4000 0.03435 0.02681 -0.1031 0.2422 0.4479
10.250 1.4100 0.03584 0.02832 -0.1023 0.2394 0.4520
10.750 1.4377 0.03824 0.03086 -0.1013 0.2348 0.4646
11.000 1.4493 0.03967 0.03234 -0.1007 0.2322 0.4727
11.250 1.4601 0.04116 0.03388 -0.1001 0.2296 0.4809
11.500 1.4678 0.04297 0.03575 -0.0994 0.2269 0.4916
11.750 1.4757 0.04476 0.03758 -0.0988 0.2243 0.5035
12.000 1.4887 0.04614 0.03906 -0.0984 0.2220 0.5183
12.500 1.5086 0.04950 0.04261 -0.0976 0.2169 0.5592
12.750 1.5159 0.05147 0.04466 -0.0971 0.2143 0.5827
13.000 1.5215 0.05360 0.04687 -0.0967 0.2118 0.6062
13.250 1.5288 0.05558 0.04894 -0.0962 0.2097 0.6305
13.500 1.5386 0.05736 0.05084 -0.0959 0.2079 0.6562
13.750 1.5478 0.05916 0.05275 -0.0956 0.2058 0.6813
14.000 1.5552 0.06118 0.05487 -0.0952 0.2036 0.7037
14.250 1.5607 0.06339 0.05715 -0.0948 0.2015 0.7224
14.500 1.5657 0.06565 0.05947 -0.0945 0.1993 0.7391
14.750 1.5681 0.06822 0.06209 -0.0941 0.1973 0.7527
15.000 1.5757 0.07024 0.06418 -0.0939 0.1956 0.7660
15.250 1.5835 0.07225 0.06628 -0.0937 0.1939 0.7797
15.500 1.5896 0.07445 0.06855 -0.0935 0.1920 0.7933
15.750 1.5957 0.07661 0.07080 -0.0933 0.1900 0.8088
16.000 1.5995 0.07903 0.07331 -0.0931 0.1880 0.8297
16.250 1.5987 0.08123 0.07572 -0.0921 0.1862 0.9638
16.500 1.6020 0.08378 0.07827 -0.0921 0.1843 1.0000
16.750 1.6075 0.08609 0.08063 -0.0920 0.1827 1.0000
17.000 1.6133 0.08840 0.08298 -0.0921 0.1810 1.0000
17.250 1.6188 0.09070 0.08533 -0.0921 0.1789 1.0000
17.500 1.6229 0.09318 0.08783 -0.0922 0.1766 1.0000
17.750 1.6224 0.09624 0.09092 -0.0924 0.1743 1.0000
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Polar data table (+)
Polar graphs
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