GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.84 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe255-il-1000000-n5.txt Download as CSV file: xf-goe255-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7588 0.08449 0.08127 -0.0780 0.9851 0.0063
-17.000 -0.7744 0.07822 0.07490 -0.0817 0.9805 0.0064
-16.750 -0.7904 0.07218 0.06875 -0.0850 0.9753 0.0064
-16.500 -0.8061 0.06647 0.06293 -0.0881 0.9702 0.0064
-16.250 -0.8231 0.06112 0.05747 -0.0907 0.9637 0.0064
-16.000 -0.8400 0.05604 0.05228 -0.0931 0.9579 0.0064
-15.750 -0.8550 0.05123 0.04736 -0.0955 0.9513 0.0065
-15.500 -0.8686 0.04672 0.04274 -0.0976 0.9442 0.0065
-15.250 -0.8794 0.04239 0.03830 -0.0998 0.9335 0.0065
-15.000 -0.8864 0.03829 0.03408 -0.1022 0.9205 0.0066
-14.750 -0.8924 0.03453 0.03009 -0.1040 0.8726 0.0066
-14.500 -0.8924 0.03115 0.02635 -0.1066 0.8180 0.0067
-14.250 -0.8866 0.02804 0.02304 -0.1098 0.7989 0.0068
-14.000 -0.8798 0.02549 0.02033 -0.1124 0.7868 0.0069
-13.500 -0.8647 0.02278 0.01738 -0.1116 0.7686 0.0071
-13.250 -0.8497 0.02187 0.01637 -0.1111 0.7612 0.0072
-13.000 -0.8324 0.02106 0.01548 -0.1107 0.7553 0.0074
-12.750 -0.8136 0.02032 0.01465 -0.1103 0.7493 0.0075
-12.250 -0.7723 0.01905 0.01321 -0.1096 0.7376 0.0078
-12.000 -0.7502 0.01849 0.01258 -0.1093 0.7320 0.0079
-11.750 -0.7285 0.01786 0.01186 -0.1090 0.7270 0.0081
-11.500 -0.7060 0.01724 0.01119 -0.1087 0.7229 0.0084
-11.250 -0.6822 0.01672 0.01062 -0.1086 0.7186 0.0087
-11.000 -0.6578 0.01627 0.01012 -0.1084 0.7143 0.0091
-10.750 -0.6329 0.01586 0.00965 -0.1083 0.7103 0.0094
-10.500 -0.6074 0.01546 0.00920 -0.1083 0.7069 0.0097
-10.250 -0.5815 0.01507 0.00877 -0.1083 0.7032 0.0101
-10.000 -0.5554 0.01472 0.00836 -0.1083 0.6991 0.0104
-9.750 -0.5296 0.01432 0.00790 -0.1082 0.6951 0.0108
-9.500 -0.5035 0.01394 0.00747 -0.1082 0.6914 0.0113
-9.250 -0.4767 0.01359 0.00709 -0.1083 0.6877 0.0119
-9.000 -0.4497 0.01328 0.00674 -0.1084 0.6834 0.0125
-8.750 -0.4224 0.01301 0.00642 -0.1085 0.6789 0.0131
-8.500 -0.3952 0.01273 0.00609 -0.1086 0.6749 0.0140
-8.250 -0.3678 0.01241 0.00576 -0.1087 0.6705 0.0152
-8.000 -0.3401 0.01215 0.00546 -0.1088 0.6655 0.0165
-7.750 -0.3126 0.01190 0.00516 -0.1089 0.6603 0.0186
-7.500 -0.2848 0.01161 0.00487 -0.1091 0.6552 0.0220
-7.250 -0.2575 0.01128 0.00456 -0.1092 0.6487 0.0306
-7.000 -0.2304 0.01094 0.00425 -0.1093 0.6424 0.0444
-6.750 -0.2028 0.01062 0.00399 -0.1095 0.6350 0.0586
-6.500 -0.1749 0.01041 0.00377 -0.1097 0.6275 0.0687
-6.250 -0.1464 0.01026 0.00360 -0.1099 0.6191 0.0757
-6.000 -0.1184 0.01008 0.00341 -0.1101 0.6083 0.0850
-5.500 -0.0636 0.00968 0.00304 -0.1103 0.5794 0.1251
-5.250 -0.0357 0.00953 0.00291 -0.1105 0.5681 0.1451
-5.000 -0.0074 0.00942 0.00280 -0.1108 0.5600 0.1608
-4.750 0.0211 0.00935 0.00272 -0.1110 0.5518 0.1727
-4.500 0.0496 0.00925 0.00263 -0.1112 0.5452 0.1863
-4.250 0.0783 0.00919 0.00255 -0.1115 0.5387 0.1956
-3.750 0.1359 0.00908 0.00242 -0.1120 0.5290 0.2149
-3.500 0.1648 0.00900 0.00235 -0.1123 0.5254 0.2266
-3.250 0.1936 0.00893 0.00229 -0.1126 0.5219 0.2411
-2.750 0.2504 0.00867 0.00222 -0.1132 0.5150 0.3077
-2.500 0.2796 0.00864 0.00223 -0.1135 0.5122 0.3269
-2.250 0.3089 0.00864 0.00223 -0.1139 0.5097 0.3362
-2.000 0.3381 0.00866 0.00224 -0.1142 0.5072 0.3453
-1.750 0.3672 0.00867 0.00225 -0.1145 0.5047 0.3530
-1.500 0.3961 0.00871 0.00227 -0.1148 0.5023 0.3594
-1.250 0.4251 0.00877 0.00229 -0.1151 0.4996 0.3631
-1.000 0.4544 0.00877 0.00230 -0.1154 0.4975 0.3667
-0.750 0.4836 0.00878 0.00232 -0.1158 0.4949 0.3702
-0.500 0.5127 0.00881 0.00234 -0.1161 0.4925 0.3735
-0.250 0.5416 0.00886 0.00237 -0.1164 0.4899 0.3769
0.000 0.5703 0.00891 0.00240 -0.1167 0.4871 0.3802
0.250 0.5987 0.00896 0.00245 -0.1169 0.4842 0.3843
0.500 0.6276 0.00899 0.00249 -0.1172 0.4819 0.3877
0.750 0.6566 0.00902 0.00252 -0.1175 0.4799 0.3911
1.000 0.6855 0.00906 0.00257 -0.1178 0.4775 0.3947
1.250 0.7142 0.00910 0.00261 -0.1181 0.4747 0.3980
1.500 0.7424 0.00915 0.00267 -0.1183 0.4710 0.4014
1.750 0.7702 0.00922 0.00274 -0.1185 0.4674 0.4056
2.000 0.7988 0.00926 0.00279 -0.1188 0.4644 0.4094
2.250 0.8272 0.00932 0.00285 -0.1190 0.4594 0.4117
2.500 0.8545 0.00941 0.00292 -0.1191 0.4528 0.4143
2.750 0.8823 0.00947 0.00299 -0.1192 0.4472 0.4178
3.000 0.9098 0.00955 0.00307 -0.1193 0.4396 0.4211
3.250 0.9364 0.00967 0.00317 -0.1193 0.4288 0.4243
3.500 0.9561 0.01014 0.00341 -0.1180 0.3800 0.4273
4.000 0.9917 0.01124 0.00416 -0.1149 0.3156 0.4344
4.250 1.0156 0.01145 0.00437 -0.1144 0.3083 0.4392
4.500 1.0395 0.01165 0.00456 -0.1138 0.3030 0.4444
4.750 1.0629 0.01185 0.00477 -0.1133 0.2983 0.4506
5.000 1.0872 0.01200 0.00496 -0.1128 0.2954 0.4589
5.250 1.1107 0.01213 0.00514 -0.1122 0.2930 0.4689
5.500 1.1321 0.01227 0.00533 -0.1112 0.2905 0.4836
5.750 1.1532 0.01241 0.00555 -0.1102 0.2879 0.5082
6.000 1.1749 0.01258 0.00583 -0.1094 0.2848 0.5466
6.250 1.1960 0.01281 0.00616 -0.1085 0.2796 0.5935
6.500 1.2188 0.01296 0.00646 -0.1080 0.2739 0.6456
6.750 1.2393 0.01319 0.00683 -0.1071 0.2674 0.7072
7.000 1.2601 0.01334 0.00720 -0.1062 0.2623 0.7896
7.250 1.2754 0.01324 0.00750 -0.1039 0.2583 1.0000
7.500 1.2947 0.01364 0.00787 -0.1028 0.2519 1.0000
7.750 1.3134 0.01407 0.00827 -0.1016 0.2432 1.0000
8.000 1.3299 0.01461 0.00876 -0.1002 0.2326 1.0000
8.250 1.3439 0.01529 0.00936 -0.0985 0.2159 1.0000
8.500 1.3444 0.01668 0.01054 -0.0949 0.1805 1.0000
8.750 1.3460 0.01810 0.01183 -0.0918 0.1573 1.0000
9.000 1.3542 0.01926 0.01293 -0.0897 0.1446 1.0000
9.250 1.3632 0.02043 0.01406 -0.0879 0.1342 1.0000
9.500 1.3699 0.02181 0.01539 -0.0859 0.1204 1.0000
9.750 1.3632 0.02424 0.01763 -0.0829 0.0896 1.0000
10.000 1.3599 0.02655 0.01984 -0.0805 0.0692 1.0000
10.250 1.3440 0.02995 0.02308 -0.0772 0.0348 1.0000
10.500 1.3398 0.03254 0.02563 -0.0751 0.0146 1.0000
10.750 1.3493 0.03407 0.02719 -0.0742 0.0126 1.0000
11.000 1.3596 0.03555 0.02871 -0.0734 0.0116 1.0000
11.250 1.3689 0.03712 0.03032 -0.0725 0.0108 1.0000
11.500 1.3769 0.03884 0.03208 -0.0716 0.0100 1.0000
11.750 1.3865 0.04043 0.03371 -0.0709 0.0097 1.0000
12.000 1.3951 0.04214 0.03547 -0.0702 0.0092 1.0000
12.250 1.4030 0.04395 0.03732 -0.0695 0.0087 1.0000
12.500 1.4102 0.04583 0.03924 -0.0688 0.0083 1.0000
12.750 1.4159 0.04790 0.04135 -0.0681 0.0079 1.0000
13.000 1.4219 0.04996 0.04347 -0.0674 0.0076 1.0000
13.250 1.4287 0.05200 0.04555 -0.0669 0.0074 1.0000
13.500 1.4348 0.05413 0.04774 -0.0664 0.0071 1.0000
13.750 1.4408 0.05629 0.04994 -0.0659 0.0069 1.0000
14.000 1.4455 0.05860 0.05231 -0.0655 0.0067 1.0000
14.250 1.4500 0.06096 0.05472 -0.0651 0.0064 1.0000
14.500 1.4542 0.06340 0.05721 -0.0647 0.0062 1.0000
14.750 1.4569 0.06604 0.05990 -0.0644 0.0060 1.0000
15.000 1.4588 0.06878 0.06271 -0.0641 0.0058 1.0000
15.250 1.4607 0.07154 0.06552 -0.0639 0.0056 1.0000
15.500 1.4632 0.07425 0.06829 -0.0637 0.0055 1.0000
15.750 1.4661 0.07693 0.07103 -0.0636 0.0054 1.0000
16.000 1.4670 0.07990 0.07406 -0.0635 0.0052 1.0000
16.250 1.4687 0.08275 0.07698 -0.0635 0.0051 1.0000
16.500 1.4683 0.08591 0.08021 -0.0635 0.0050 1.0000
16.750 1.4687 0.08895 0.08331 -0.0636 0.0049 1.0000
17.000 1.4677 0.09222 0.08665 -0.0638 0.0048 1.0000
17.250 1.4666 0.09552 0.09002 -0.0640 0.0047 1.0000
17.500 1.4648 0.09896 0.09353 -0.0643 0.0046 1.0000
17.750 1.4621 0.10255 0.09719 -0.0647 0.0045 1.0000
18.000 1.4593 0.10616 0.10086 -0.0652 0.0044 1.0000
18.250 1.4541 0.11015 0.10493 -0.0658 0.0043 1.0000
18.500 1.4486 0.11423 0.10909 -0.0665 0.0042 1.0000
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