GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 500,000 Max Cl/Cd: 102.31 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe553-il-500000-n5.txt Download as CSV file: xf-goe553-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3447 0.09291 0.09047 -0.0452 1.0000 0.0210
-10.000 -0.4758 0.02801 0.02392 -0.1130 0.8973 0.0243
-9.750 -0.4623 0.02545 0.02084 -0.1134 0.8681 0.0248
-9.500 -0.4431 0.02430 0.01949 -0.1129 0.8387 0.0250
-9.250 -0.4230 0.02358 0.01857 -0.1122 0.8068 0.0252
-9.000 -0.4028 0.02286 0.01763 -0.1114 0.7749 0.0255
-8.750 -0.3824 0.02203 0.01656 -0.1107 0.7482 0.0257
-8.500 -0.3609 0.02127 0.01559 -0.1101 0.7254 0.0260
-8.250 -0.3386 0.02049 0.01459 -0.1095 0.7069 0.0263
-8.000 -0.3155 0.01973 0.01363 -0.1090 0.6922 0.0266
-7.750 -0.2919 0.01897 0.01268 -0.1086 0.6797 0.0269
-7.500 -0.2675 0.01829 0.01182 -0.1082 0.6687 0.0274
-7.250 -0.2426 0.01765 0.01100 -0.1078 0.6597 0.0279
-7.000 -0.2173 0.01702 0.01021 -0.1075 0.6512 0.0282
-6.750 -0.1917 0.01645 0.00948 -0.1071 0.6441 0.0285
-6.500 -0.1655 0.01594 0.00885 -0.1068 0.6372 0.0287
-6.250 -0.1399 0.01534 0.00814 -0.1065 0.6307 0.0290
-6.000 -0.1139 0.01477 0.00751 -0.1062 0.6248 0.0293
-5.750 -0.0875 0.01433 0.00702 -0.1060 0.6188 0.0296
-5.500 -0.0610 0.01398 0.00661 -0.1057 0.6127 0.0300
-5.250 -0.0341 0.01365 0.00624 -0.1054 0.6074 0.0304
-5.000 -0.0070 0.01335 0.00590 -0.1052 0.6016 0.0309
-4.750 0.0199 0.01307 0.00556 -0.1050 0.5959 0.0314
-4.500 0.0469 0.01279 0.00523 -0.1047 0.5908 0.0319
-4.250 0.0743 0.01249 0.00489 -0.1045 0.5856 0.0324
-4.000 0.1016 0.01224 0.00459 -0.1043 0.5803 0.0328
-3.750 0.1288 0.01203 0.00432 -0.1041 0.5754 0.0332
-3.500 0.1565 0.01180 0.00407 -0.1039 0.5707 0.0336
-3.250 0.1838 0.01150 0.00375 -0.1038 0.5651 0.0342
-3.000 0.2112 0.01131 0.00353 -0.1036 0.5596 0.0349
-2.750 0.2389 0.01115 0.00335 -0.1034 0.5548 0.0356
-2.500 0.2669 0.01100 0.00319 -0.1033 0.5494 0.0366
-2.250 0.2946 0.01089 0.00305 -0.1032 0.5434 0.0377
-2.000 0.3224 0.01079 0.00291 -0.1030 0.5375 0.0387
-1.750 0.3503 0.01065 0.00276 -0.1029 0.5309 0.0400
-1.500 0.3779 0.01056 0.00264 -0.1027 0.5244 0.0416
-1.250 0.4059 0.01049 0.00255 -0.1026 0.5183 0.0437
-1.000 0.4338 0.01042 0.00246 -0.1024 0.5113 0.0468
-0.750 0.4613 0.01036 0.00238 -0.1022 0.5040 0.0529
-0.500 0.4886 0.01015 0.00232 -0.1021 0.4943 0.1015
-0.250 0.5157 0.01004 0.00228 -0.1020 0.4844 0.1400
0.000 0.5419 0.00969 0.00224 -0.1019 0.4740 0.2682
0.250 0.5682 0.00935 0.00227 -0.1018 0.4647 0.4087
0.500 0.5947 0.00931 0.00235 -0.1015 0.4555 0.4751
0.750 0.6218 0.00931 0.00243 -0.1012 0.4463 0.5207
1.000 0.6484 0.00936 0.00252 -0.1008 0.4382 0.5608
1.250 0.6753 0.00939 0.00262 -0.1005 0.4303 0.5926
1.500 0.7020 0.00949 0.00270 -0.1002 0.4225 0.6105
1.750 0.7290 0.00956 0.00278 -0.0999 0.4141 0.6246
2.000 0.7555 0.00968 0.00287 -0.0996 0.4058 0.6379
2.500 0.8090 0.00990 0.00306 -0.0990 0.3913 0.6605
2.750 0.8359 0.00998 0.00317 -0.0987 0.3855 0.6727
3.000 0.8624 0.01007 0.00328 -0.0984 0.3793 0.6905
3.250 0.8882 0.01018 0.00342 -0.0980 0.3735 0.7113
3.500 0.9145 0.01025 0.00354 -0.0976 0.3674 0.7319
3.750 0.9400 0.01035 0.00368 -0.0971 0.3607 0.7553
4.000 0.9646 0.01040 0.00382 -0.0964 0.3545 0.7912
4.250 0.9943 0.01024 0.00396 -0.0966 0.3474 0.9280
4.500 1.0242 0.01044 0.00411 -0.0972 0.3417 1.0000
4.750 1.0507 0.01060 0.00426 -0.0969 0.3373 1.0000
5.000 1.0768 0.01077 0.00442 -0.0966 0.3320 1.0000
5.250 1.1020 0.01100 0.00461 -0.0962 0.3259 1.0000
5.500 1.1278 0.01119 0.00479 -0.0958 0.3208 1.0000
5.750 1.1535 0.01137 0.00498 -0.0954 0.3159 1.0000
6.000 1.1785 0.01160 0.00518 -0.0950 0.3108 1.0000
6.250 1.2034 0.01182 0.00539 -0.0945 0.3062 1.0000
6.500 1.2287 0.01201 0.00561 -0.0941 0.3012 1.0000
6.750 1.2529 0.01226 0.00584 -0.0935 0.2952 1.0000
7.000 1.2767 0.01252 0.00609 -0.0929 0.2871 1.0000
7.250 1.2996 0.01283 0.00636 -0.0921 0.2777 1.0000
7.500 1.3227 0.01311 0.00663 -0.0914 0.2680 1.0000
7.750 1.3446 0.01345 0.00694 -0.0905 0.2577 1.0000
8.000 1.3656 0.01383 0.00728 -0.0895 0.2459 1.0000
8.250 1.3853 0.01426 0.00765 -0.0883 0.2313 1.0000
8.500 1.4030 0.01478 0.00809 -0.0868 0.2138 1.0000
8.750 1.4194 0.01534 0.00857 -0.0851 0.1991 1.0000
9.000 1.4343 0.01587 0.00906 -0.0832 0.1891 1.0000
9.250 1.4491 0.01635 0.00953 -0.0811 0.1826 1.0000
9.500 1.4626 0.01688 0.01006 -0.0790 0.1770 1.0000
9.750 1.4777 0.01735 0.01056 -0.0771 0.1730 1.0000
10.000 1.4917 0.01788 0.01112 -0.0751 0.1689 1.0000
10.250 1.5043 0.01849 0.01174 -0.0731 0.1651 1.0000
10.500 1.5161 0.01916 0.01243 -0.0710 0.1614 1.0000
10.750 1.5302 0.01974 0.01307 -0.0693 0.1581 1.0000
11.000 1.5426 0.02044 0.01381 -0.0675 0.1546 1.0000
11.250 1.5527 0.02128 0.01469 -0.0656 0.1509 1.0000
11.500 1.5609 0.02229 0.01572 -0.0637 0.1467 1.0000
11.750 1.5740 0.02306 0.01656 -0.0623 0.1425 1.0000
12.000 1.5822 0.02418 0.01771 -0.0606 0.1361 1.0000
12.250 1.5898 0.02541 0.01897 -0.0591 0.1294 1.0000
12.500 1.5935 0.02700 0.02054 -0.0575 0.1156 1.0000
12.750 1.5777 0.03030 0.02363 -0.0552 0.0858 1.0000
13.000 1.5697 0.03325 0.02656 -0.0538 0.0756 1.0000
13.250 1.5668 0.03592 0.02927 -0.0529 0.0702 1.0000
13.500 1.5647 0.03862 0.03203 -0.0522 0.0659 1.0000
13.750 1.5642 0.04125 0.03472 -0.0517 0.0629 1.0000
14.000 1.5620 0.04412 0.03766 -0.0514 0.0605 1.0000
14.250 1.5604 0.04699 0.04059 -0.0511 0.0583 1.0000
14.500 1.5602 0.04978 0.04346 -0.0510 0.0566 1.0000
14.750 1.5580 0.05286 0.04663 -0.0509 0.0546 1.0000
15.000 1.5539 0.05624 0.05007 -0.0510 0.0528 1.0000
15.250 1.5492 0.05980 0.05371 -0.0513 0.0513 1.0000
15.500 1.5474 0.06309 0.05710 -0.0517 0.0499 1.0000
15.750 1.5451 0.06655 0.06064 -0.0522 0.0484 1.0000
16.000 1.5413 0.07027 0.06444 -0.0528 0.0468 1.0000
16.250 1.5365 0.07423 0.06847 -0.0536 0.0454 1.0000
16.500 1.5300 0.07851 0.07283 -0.0546 0.0441 1.0000
16.750 1.5273 0.08232 0.07674 -0.0555 0.0427 1.0000
17.000 1.5238 0.08631 0.08082 -0.0565 0.0415 1.0000
17.250 1.5189 0.09059 0.08518 -0.0578 0.0399 1.0000
17.500 1.5124 0.09516 0.08983 -0.0592 0.0385 1.0000
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