GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 500,000 Max Cl/Cd: 68.11 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417a-il-500000-n5.txt Download as CSV file: xf-goe417a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417A (GEW. PLATTE) 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3918 0.12889 0.12649 -0.0171 1.0000 0.0094
-11.000 -0.3892 0.12659 0.12421 -0.0169 1.0000 0.0095
-10.750 -0.3874 0.12417 0.12181 -0.0166 1.0000 0.0095
-10.500 -0.3821 0.12307 0.12071 -0.0161 1.0000 0.0104
-10.250 -0.3724 0.11997 0.11761 -0.0180 0.9994 0.0113
-10.000 -0.3626 0.11646 0.11410 -0.0203 0.9985 0.0115
-9.750 -0.3520 0.11318 0.11081 -0.0227 0.9974 0.0114
-9.500 -0.3410 0.10982 0.10746 -0.0252 0.9960 0.0121
-9.250 -0.3289 0.10698 0.10462 -0.0276 0.9948 0.0124
-9.000 -0.3177 0.10401 0.10165 -0.0298 0.9935 0.0125
-8.750 -0.3075 0.10121 0.09885 -0.0318 0.9917 0.0127
-8.500 -0.2956 0.09853 0.09617 -0.0340 0.9897 0.0141
-8.250 -0.2833 0.09541 0.09305 -0.0369 0.9876 0.0139
-8.000 -0.2659 0.09305 0.09068 -0.0401 0.9858 0.0171
-7.750 -0.2528 0.08991 0.08753 -0.0433 0.9824 0.0172
-7.500 -0.2375 0.08660 0.08421 -0.0468 0.9785 0.0173
-7.250 -0.2143 0.08281 0.08040 -0.0529 0.9760 0.0175
-6.750 -0.1801 0.07694 0.07452 -0.0585 0.9702 0.0181
-6.500 -0.1593 0.07420 0.07177 -0.0621 0.9676 0.0191
-6.250 -0.1331 0.07101 0.06854 -0.0671 0.9657 0.0200
-6.000 -0.1017 0.06765 0.06513 -0.0735 0.9641 0.0202
-5.750 -0.0743 0.06516 0.06258 -0.0787 0.9593 0.0203
-5.500 -0.0439 0.06241 0.05977 -0.0841 0.9565 0.0204
-5.250 -0.0080 0.05958 0.05687 -0.0904 0.9545 0.0204
-5.000 0.0276 0.05659 0.05381 -0.0961 0.9530 0.0204
-4.750 0.0423 0.05336 0.05059 -0.0961 0.9492 0.0205
-4.500 0.0614 0.05067 0.04788 -0.0971 0.9449 0.0206
-4.250 0.0878 0.04803 0.04520 -0.0998 0.9420 0.0207
-4.000 0.1184 0.04555 0.04267 -0.1033 0.9397 0.0209
-3.750 0.1378 0.04371 0.04081 -0.1038 0.9338 0.0211
-3.500 0.1654 0.04164 0.03869 -0.1059 0.9300 0.0215
-3.250 0.1967 0.03952 0.03650 -0.1087 0.9270 0.0219
-3.000 0.2194 0.03780 0.03472 -0.1092 0.9200 0.0222
-2.750 0.2504 0.03588 0.03273 -0.1113 0.9137 0.0227
-2.500 0.2765 0.03439 0.03116 -0.1119 0.9056 0.0231
-2.250 0.3069 0.03272 0.02941 -0.1134 0.8987 0.0233
-2.000 0.3320 0.03127 0.02787 -0.1135 0.8904 0.0233
-1.750 0.3613 0.02973 0.02623 -0.1144 0.8815 0.0234
-1.500 0.3871 0.02834 0.02474 -0.1144 0.8687 0.0234
-1.250 0.4151 0.02697 0.02324 -0.1146 0.8517 0.0234
-1.000 0.4422 0.02568 0.02177 -0.1146 0.8226 0.0235
-0.750 0.4680 0.02456 0.02034 -0.1140 0.7750 0.0235
-0.500 0.4899 0.02364 0.01912 -0.1126 0.7379 0.0235
-0.250 0.5119 0.02272 0.01797 -0.1111 0.7130 0.0236
0.000 0.5339 0.02185 0.01687 -0.1096 0.6887 0.0236
0.250 0.5552 0.02103 0.01586 -0.1081 0.6652 0.0236
0.500 0.5744 0.01965 0.01432 -0.1066 0.6418 0.0238
0.750 0.5924 0.01863 0.01317 -0.1051 0.6154 0.0240
1.000 0.6107 0.01799 0.01237 -0.1035 0.5857 0.0245
1.250 0.6311 0.01745 0.01167 -0.1020 0.5613 0.0249
1.500 0.6528 0.01692 0.01097 -0.1005 0.5422 0.0253
1.750 0.6748 0.01642 0.01031 -0.0991 0.5237 0.0255
2.000 0.6973 0.01595 0.00970 -0.0978 0.5065 0.0258
2.250 0.7202 0.01552 0.00913 -0.0965 0.4908 0.0262
2.500 0.7427 0.01522 0.00866 -0.0950 0.4683 0.0269
2.750 0.7651 0.01521 0.00843 -0.0934 0.4356 0.0276
3.000 0.7851 0.01523 0.00814 -0.0915 0.3822 0.0277
3.250 0.8020 0.01545 0.00791 -0.0892 0.3005 0.0278
3.500 0.8193 0.01573 0.00775 -0.0871 0.2284 0.0279
3.750 0.8412 0.01560 0.00745 -0.0858 0.2073 0.0279
4.000 0.8639 0.01541 0.00712 -0.0846 0.1938 0.0280
6.000 1.0363 0.01552 0.00645 -0.0749 0.0372 0.0407
6.250 1.0575 0.01564 0.00658 -0.0734 0.0341 0.0321
6.500 1.0775 0.01582 0.00678 -0.0718 0.0316 0.0304
6.750 1.0967 0.01613 0.00711 -0.0700 0.0290 0.0292
7.000 1.1161 0.01642 0.00745 -0.0684 0.0279 0.0286
7.250 1.1355 0.01668 0.00776 -0.0667 0.0272 0.0284
7.500 1.1543 0.01697 0.00812 -0.0650 0.0263 0.0283
7.750 1.1719 0.01726 0.00848 -0.0630 0.0253 0.0286
8.000 1.1887 0.01758 0.00885 -0.0609 0.0243 0.0293
8.250 1.2050 0.01794 0.00923 -0.0587 0.0232 0.0309
8.500 1.2204 0.01840 0.00972 -0.0564 0.0222 0.0338
8.750 1.2339 0.01900 0.01035 -0.0538 0.0213 0.0350
9.000 1.2435 0.01987 0.01131 -0.0505 0.0204 0.0355
9.250 1.2588 0.02035 0.01185 -0.0483 0.0201 0.0361
9.500 1.2735 0.02086 0.01243 -0.0461 0.0196 0.0379
9.750 1.2876 0.02139 0.01308 -0.0438 0.0191 0.1178
10.000 1.4528 0.02269 0.01556 -0.0762 0.0158 1.0000
10.250 1.4586 0.02351 0.01642 -0.0724 0.0151 1.0000
10.500 1.4678 0.02416 0.01715 -0.0692 0.0147 1.0000
10.750 1.4780 0.02478 0.01786 -0.0662 0.0143 1.0000
11.000 1.4897 0.02532 0.01849 -0.0636 0.0136 1.0000
11.250 1.5005 0.02594 0.01918 -0.0610 0.0129 1.0000
11.500 1.5121 0.02651 0.01980 -0.0585 0.0122 1.0000
11.750 1.5225 0.02719 0.02053 -0.0560 0.0117 1.0000
12.000 1.5314 0.02799 0.02138 -0.0533 0.0112 1.0000
12.250 1.5362 0.02913 0.02259 -0.0503 0.0106 1.0000
12.500 1.5425 0.03020 0.02378 -0.0475 0.0104 1.0000
12.750 1.5486 0.03131 0.02502 -0.0448 0.0099 1.0000
13.000 1.5553 0.03241 0.02623 -0.0424 0.0094 1.0000
13.250 1.5599 0.03372 0.02765 -0.0398 0.0090 1.0000
13.500 1.5668 0.03486 0.02887 -0.0377 0.0084 1.0000
13.750 1.5708 0.03630 0.03040 -0.0355 0.0082 1.0000
14.000 1.5737 0.03791 0.03210 -0.0334 0.0079 1.0000
14.250 1.5736 0.03986 0.03414 -0.0314 0.0074 1.0000
14.500 1.5720 0.04210 0.03651 -0.0295 0.0071 1.0000
14.750 1.5718 0.04429 0.03885 -0.0280 0.0069 1.0000
15.000 1.5671 0.04713 0.04184 -0.0267 0.0068 1.0000
15.250 1.5633 0.05003 0.04489 -0.0257 0.0066 1.0000
15.500 1.5581 0.05323 0.04824 -0.0251 0.0064 1.0000
15.750 1.5517 0.05677 0.05193 -0.0249 0.0062 1.0000
16.000 1.5457 0.06046 0.05576 -0.0250 0.0060 1.0000
16.250 1.5416 0.06401 0.05943 -0.0254 0.0059 1.0000
16.500 1.5295 0.06894 0.06454 -0.0264 0.0059 1.0000
16.750 1.5214 0.07348 0.06921 -0.0276 0.0057 1.0000
17.000 1.5120 0.07837 0.07422 -0.0290 0.0055 1.0000
17.250 1.4953 0.08463 0.08064 -0.0312 0.0055 1.0000
17.500 1.4801 0.09086 0.08703 -0.0336 0.0055 1.0000
17.750 1.4626 0.09774 0.09405 -0.0364 0.0054 1.0000
18.000 1.4418 0.10554 0.10202 -0.0399 0.0054 1.0000
18.250 1.4230 0.11328 0.10990 -0.0436 0.0053 1.0000
18.500 1.4048 0.12108 0.11784 -0.0473 0.0053 1.0000
18.750 1.3822 0.13007 0.12699 -0.0519 0.0054 1.0000
19.000 1.3600 0.13929 0.13635 -0.0567 0.0054 1.0000
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