GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 496 AIRFOIL (goe496-il) Reynolds number: 50,000 Max Cl/Cd: 40.97 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe496-il-50000-n5.txt Download as CSV file: xf-goe496-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 496 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3283 0.10217 0.09523 -0.0366 1.0000 0.0920
-8.000 -0.3341 0.09977 0.09292 -0.0353 1.0000 0.0899
-7.500 -0.3820 0.09498 0.08843 -0.0339 1.0000 0.0823
-7.250 -0.3850 0.09268 0.08620 -0.0322 1.0000 0.0816
-7.000 -0.3904 0.09029 0.08388 -0.0311 1.0000 0.0809
-6.750 -0.3960 0.08773 0.08139 -0.0306 1.0000 0.0803
-6.500 -0.4008 0.08488 0.07859 -0.0308 1.0000 0.0797
-6.250 -0.3947 0.08077 0.07450 -0.0346 0.9973 0.0794
-6.000 -0.3683 0.07384 0.06744 -0.0462 0.9889 0.0808
-5.750 -0.3379 0.06597 0.05938 -0.0587 0.9811 0.0814
-5.500 -0.3031 0.05805 0.05115 -0.0704 0.9745 0.0812
-5.250 -0.2640 0.04963 0.04216 -0.0827 0.9679 0.0815
-5.000 -0.2238 0.04411 0.03605 -0.0912 0.9624 0.0840
-4.750 -0.1903 0.04242 0.03423 -0.0941 0.9558 0.0876
-4.500 -0.1511 0.03868 0.02990 -0.0996 0.9499 0.0903
-4.250 -0.1105 0.03539 0.02592 -0.1044 0.9444 0.0932
-4.000 -0.0720 0.03301 0.02291 -0.1077 0.9387 0.0967
-3.750 -0.0388 0.03211 0.02196 -0.1095 0.9317 0.1025
-3.500 -0.0026 0.03075 0.02011 -0.1117 0.9253 0.1105
-3.250 0.0309 0.02976 0.01902 -0.1132 0.9183 0.1169
-3.000 0.0655 0.02877 0.01779 -0.1148 0.9118 0.1275
-2.750 0.0978 0.02813 0.01712 -0.1160 0.9043 0.1438
-2.500 0.1338 0.02743 0.01628 -0.1177 0.8981 0.1660
-2.250 0.1641 0.02710 0.01601 -0.1185 0.8897 0.1905
-2.000 0.2040 0.02683 0.01572 -0.1209 0.8846 0.2242
-1.750 0.2296 0.02684 0.01576 -0.1208 0.8745 0.2545
-1.500 0.2691 0.02654 0.01545 -0.1229 0.8694 0.2862
-1.250 0.2955 0.02639 0.01529 -0.1228 0.8597 0.3089
-1.000 0.3341 0.02603 0.01496 -0.1246 0.8542 0.3429
-0.750 0.3609 0.02598 0.01497 -0.1245 0.8450 0.3806
-0.500 0.3973 0.02573 0.01481 -0.1258 0.8390 0.4287
-0.250 0.4247 0.02568 0.01484 -0.1257 0.8301 0.4724
0.000 0.4579 0.02543 0.01472 -0.1264 0.8235 0.5245
0.250 0.4839 0.02528 0.01481 -0.1258 0.8151 0.5855
0.500 0.5102 0.02479 0.01474 -0.1248 0.8079 0.7039
0.750 0.5336 0.02446 0.01466 -0.1235 0.7986 1.0000
1.000 0.5684 0.02460 0.01458 -0.1247 0.7915 1.0000
1.250 0.5958 0.02496 0.01477 -0.1248 0.7823 1.0000
1.500 0.6296 0.02509 0.01477 -0.1256 0.7754 1.0000
1.750 0.6549 0.02550 0.01508 -0.1253 0.7658 1.0000
2.000 0.6890 0.02561 0.01509 -0.1261 0.7592 1.0000
2.250 0.7122 0.02609 0.01553 -0.1255 0.7490 1.0000
2.500 0.7473 0.02613 0.01551 -0.1263 0.7428 1.0000
2.750 0.7687 0.02668 0.01606 -0.1254 0.7319 1.0000
3.000 0.8054 0.02662 0.01597 -0.1263 0.7261 1.0000
3.250 0.8252 0.02722 0.01658 -0.1251 0.7144 1.0000
3.500 0.8519 0.02744 0.01682 -0.1245 0.7036 1.0000
3.750 0.8872 0.02709 0.01646 -0.1247 0.6930 1.0000
4.000 0.9161 0.02696 0.01634 -0.1240 0.6795 1.0000
4.250 0.9409 0.02703 0.01646 -0.1229 0.6652 1.0000
4.500 0.9650 0.02723 0.01671 -0.1218 0.6518 1.0000
4.750 0.9901 0.02745 0.01699 -0.1209 0.6396 1.0000
5.000 1.0182 0.02752 0.01714 -0.1203 0.6279 1.0000
5.250 1.0474 0.02751 0.01720 -0.1199 0.6158 1.0000
5.500 1.0696 0.02784 0.01763 -0.1186 0.6017 1.0000
5.750 1.0927 0.02811 0.01802 -0.1174 0.5871 1.0000
6.000 1.1161 0.02835 0.01836 -0.1162 0.5720 1.0000
6.250 1.1395 0.02860 0.01872 -0.1149 0.5563 1.0000
6.500 1.1628 0.02884 0.01905 -0.1137 0.5397 1.0000
6.750 1.1862 0.02908 0.01940 -0.1124 0.5222 1.0000
7.000 1.2069 0.02946 0.01988 -0.1108 0.5036 1.0000
7.250 1.2244 0.03001 0.02055 -0.1089 0.4831 1.0000
7.500 1.2434 0.03049 0.02112 -0.1071 0.4624 1.0000
7.750 1.2640 0.03093 0.02163 -0.1055 0.4421 1.0000
8.000 1.2785 0.03171 0.02252 -0.1033 0.4203 1.0000
8.250 1.2951 0.03241 0.02328 -0.1014 0.3996 1.0000
8.500 1.3100 0.03314 0.02401 -0.0992 0.3782 1.0000
8.750 1.3184 0.03407 0.02495 -0.0963 0.3553 1.0000
9.000 1.3256 0.03501 0.02580 -0.0933 0.3328 1.0000
9.250 1.3296 0.03625 0.02708 -0.0902 0.3106 1.0000
9.500 1.3344 0.03756 0.02834 -0.0874 0.2904 1.0000
9.750 1.3385 0.03903 0.02978 -0.0848 0.2715 1.0000
10.000 1.3404 0.04073 0.03154 -0.0822 0.2524 1.0000
10.250 1.3407 0.04263 0.03348 -0.0798 0.2334 1.0000
10.500 1.3390 0.04476 0.03564 -0.0775 0.2143 1.0000
10.750 1.3350 0.04721 0.03806 -0.0755 0.1949 1.0000
11.000 1.3304 0.04995 0.04093 -0.0739 0.1729 1.0000
11.250 1.3240 0.05303 0.04401 -0.0726 0.1519 1.0000
11.500 1.3181 0.05635 0.04735 -0.0716 0.1315 1.0000
11.750 1.3117 0.05994 0.05089 -0.0709 0.1148 1.0000
12.000 1.3054 0.06371 0.05461 -0.0703 0.1020 1.0000
12.250 1.2992 0.06763 0.05847 -0.0700 0.0924 1.0000
12.500 1.2936 0.07160 0.06244 -0.0699 0.0846 1.0000
12.750 1.2907 0.07543 0.06635 -0.0697 0.0777 1.0000
13.000 1.2865 0.07942 0.07035 -0.0698 0.0723 1.0000
13.250 1.2852 0.08322 0.07429 -0.0698 0.0674 1.0000
13.500 1.2848 0.08697 0.07818 -0.0699 0.0632 1.0000
13.750 1.2848 0.09057 0.08180 -0.0700 0.0600 1.0000
14.000 1.2858 0.09436 0.08578 -0.0702 0.0570 1.0000
14.250 1.2846 0.09861 0.09030 -0.0709 0.0542 1.0000
14.500 1.2831 0.10286 0.09477 -0.0718 0.0518 1.0000
14.750 1.2835 0.10673 0.09873 -0.0725 0.0498 1.0000
15.000 1.2888 0.10989 0.10190 -0.0725 0.0481 1.0000
15.250 1.2807 0.11582 0.10818 -0.0749 0.0473 1.0000
15.500 1.2697 0.12247 0.11514 -0.0780 0.0467 1.0000
15.750 1.2562 0.12993 0.12288 -0.0820 0.0462 1.0000
16.000 1.2399 0.13845 0.13167 -0.0871 0.0460 1.0000
16.250 1.2203 0.14842 0.14188 -0.0934 0.0461 1.0000
16.500 1.1976 0.16020 0.15381 -0.1010 0.0465 1.0000
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