GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 200,000 Max Cl/Cd: 76.49 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe178-il-200000-n5.txt Download as CSV file: xf-goe178-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 178 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3644 0.09043 0.08710 -0.0195 1.0000 0.0208
-7.750 -0.3607 0.08719 0.08390 -0.0211 1.0000 0.0212
-7.500 -0.3577 0.08421 0.08097 -0.0227 1.0000 0.0221
-7.250 -0.3534 0.08060 0.07741 -0.0256 1.0000 0.0231
-7.000 -0.3491 0.07659 0.07344 -0.0291 1.0000 0.0236
-6.750 -0.3454 0.07254 0.06942 -0.0322 1.0000 0.0237
-6.500 -0.3213 0.06586 0.06269 -0.0420 0.9925 0.0241
-6.250 -0.2837 0.05494 0.05160 -0.0586 0.9819 0.0261
-6.000 -0.2562 0.05365 0.05027 -0.0611 0.9740 0.0277
-5.750 -0.2220 0.04782 0.04424 -0.0691 0.9639 0.0286
-5.500 -0.1875 0.04147 0.03763 -0.0764 0.9523 0.0299
-5.250 -0.1522 0.03356 0.02921 -0.0833 0.9401 0.0322
-5.000 -0.1195 0.02569 0.02047 -0.0879 0.9271 0.0333
-4.750 -0.0893 0.02226 0.01635 -0.0896 0.9107 0.0348
-4.500 -0.0603 0.01973 0.01335 -0.0904 0.8914 0.0355
-4.250 -0.0317 0.01816 0.01143 -0.0907 0.8686 0.0361
-4.000 -0.0040 0.01701 0.00995 -0.0905 0.8439 0.0367
-3.750 0.0227 0.01621 0.00887 -0.0900 0.8184 0.0377
-3.500 0.0492 0.01561 0.00803 -0.0895 0.7923 0.0390
-3.250 0.0760 0.01494 0.00710 -0.0891 0.7654 0.0397
-3.000 0.1029 0.01434 0.00624 -0.0886 0.7369 0.0401
-2.750 0.1298 0.01386 0.00554 -0.0882 0.7064 0.0406
-2.500 0.1566 0.01349 0.00495 -0.0878 0.6747 0.0413
-2.250 0.1836 0.01322 0.00444 -0.0875 0.6448 0.0421
-2.000 0.2109 0.01301 0.00403 -0.0873 0.6182 0.0431
-1.750 0.2382 0.01287 0.00369 -0.0871 0.5951 0.0441
-1.500 0.2659 0.01273 0.00341 -0.0870 0.5751 0.0458
-1.250 0.2937 0.01264 0.00322 -0.0869 0.5586 0.0484
-1.000 0.3215 0.01258 0.00311 -0.0868 0.5451 0.0538
-0.750 0.3494 0.01256 0.00305 -0.0868 0.5339 0.0673
-0.500 0.3774 0.01256 0.00297 -0.0868 0.5238 0.0815
-0.250 0.4054 0.01255 0.00291 -0.0868 0.5151 0.0936
0.000 0.4332 0.01256 0.00286 -0.0867 0.5070 0.1040
0.250 0.4613 0.01258 0.00285 -0.0868 0.4996 0.1131
0.500 0.4891 0.01260 0.00285 -0.0868 0.4929 0.1268
0.750 0.5171 0.01251 0.00291 -0.0869 0.4860 0.1780
1.000 0.5448 0.01241 0.00296 -0.0870 0.4786 0.2518
1.250 0.5717 0.01197 0.00309 -0.0871 0.4717 0.4667
1.750 0.6212 0.01109 0.00317 -0.0853 0.4588 1.0000
2.000 0.6491 0.01124 0.00325 -0.0852 0.4522 1.0000
2.250 0.6768 0.01142 0.00335 -0.0852 0.4470 1.0000
2.500 0.7047 0.01159 0.00347 -0.0852 0.4422 1.0000
2.750 0.7326 0.01175 0.00360 -0.0852 0.4372 1.0000
3.000 0.7602 0.01194 0.00376 -0.0851 0.4329 1.0000
3.250 0.7878 0.01213 0.00392 -0.0851 0.4284 1.0000
3.500 0.8154 0.01228 0.00409 -0.0850 0.4217 1.0000
3.750 0.8426 0.01248 0.00424 -0.0849 0.4136 1.0000
4.000 0.8698 0.01262 0.00440 -0.0848 0.4041 1.0000
4.250 0.8970 0.01280 0.00458 -0.0847 0.3962 1.0000
4.500 0.9243 0.01297 0.00480 -0.0846 0.3893 1.0000
4.750 0.9514 0.01317 0.00502 -0.0845 0.3829 1.0000
5.000 0.9786 0.01334 0.00526 -0.0844 0.3756 1.0000
5.250 1.0054 0.01355 0.00552 -0.0843 0.3690 1.0000
5.500 1.0322 0.01373 0.00575 -0.0841 0.3581 1.0000
5.750 1.0584 0.01390 0.00594 -0.0839 0.3373 1.0000
6.000 1.0839 0.01417 0.00615 -0.0836 0.3083 1.0000
6.250 1.1083 0.01458 0.00647 -0.0832 0.2765 1.0000
6.500 1.1310 0.01527 0.00694 -0.0827 0.2393 1.0000
6.750 1.1535 0.01600 0.00754 -0.0821 0.2071 1.0000
7.250 1.1845 0.01936 0.01001 -0.0797 0.0494 1.0000
7.500 1.2058 0.02019 0.01087 -0.0789 0.0280 1.0000
7.750 1.2257 0.02115 0.01178 -0.0779 0.0211 1.0000
8.000 1.2458 0.02202 0.01277 -0.0770 0.0186 1.0000
8.250 1.2647 0.02297 0.01388 -0.0759 0.0166 1.0000
8.500 1.2816 0.02406 0.01513 -0.0746 0.0154 1.0000
8.750 1.2956 0.02535 0.01661 -0.0729 0.0145 1.0000
9.000 1.3051 0.02692 0.01835 -0.0708 0.0138 1.0000
9.250 1.3089 0.02881 0.02041 -0.0681 0.0133 1.0000
9.500 1.3146 0.03026 0.02198 -0.0656 0.0129 1.0000
9.750 1.3193 0.03173 0.02358 -0.0631 0.0125 1.0000
10.000 1.3230 0.03341 0.02539 -0.0610 0.0119 1.0000
10.250 1.3251 0.03539 0.02749 -0.0591 0.0115 1.0000
10.500 1.3261 0.03764 0.02987 -0.0575 0.0111 1.0000
10.750 1.3267 0.04013 0.03248 -0.0564 0.0109 1.0000
11.000 1.3276 0.04276 0.03523 -0.0555 0.0107 1.0000
11.250 1.3287 0.04547 0.03805 -0.0547 0.0104 1.0000
11.500 1.3299 0.04824 0.04097 -0.0540 0.0102 1.0000
11.750 1.3315 0.05103 0.04387 -0.0534 0.0100 1.0000
12.000 1.3332 0.05385 0.04680 -0.0528 0.0098 1.0000
12.250 1.3349 0.05670 0.04976 -0.0522 0.0097 1.0000
12.500 1.3366 0.05959 0.05276 -0.0516 0.0095 1.0000
12.750 1.3381 0.06254 0.05582 -0.0510 0.0094 1.0000
13.000 1.3390 0.06562 0.05900 -0.0504 0.0091 1.0000
13.250 1.3395 0.06894 0.06242 -0.0491 0.0089 1.0000
13.500 1.3361 0.07275 0.06643 -0.0494 0.0087 1.0000
13.750 1.3312 0.07682 0.07073 -0.0506 0.0086 1.0000
14.000 1.3257 0.08111 0.07523 -0.0517 0.0084 1.0000
14.250 1.3187 0.08571 0.08005 -0.0530 0.0083 1.0000
14.500 1.3108 0.09060 0.08515 -0.0545 0.0082 1.0000
14.750 1.3017 0.09584 0.09059 -0.0564 0.0081 1.0000
15.000 1.2914 0.10144 0.09640 -0.0585 0.0080 1.0000
15.250 1.2802 0.10736 0.10253 -0.0610 0.0080 1.0000
15.500 1.2681 0.11371 0.10907 -0.0640 0.0080 1.0000
15.750 1.2556 0.12036 0.11591 -0.0674 0.0080 1.0000
16.000 1.2423 0.12743 0.12317 -0.0712 0.0080 1.0000
16.250 1.2286 0.13494 0.13085 -0.0755 0.0080 1.0000
16.500 1.2149 0.14284 0.13893 -0.0803 0.0080 1.0000
16.750 1.2011 0.15124 0.14749 -0.0855 0.0081 1.0000
17.000 1.1868 0.16030 0.15671 -0.0913 0.0081 1.0000
17.250 1.1725 0.16997 0.16651 -0.0976 0.0082 1.0000
17.500 1.1576 0.18063 0.17729 -0.1044 0.0083 1.0000
17.750 1.1437 0.19196 0.18870 -0.1115 0.0085 1.0000
18.000 1.1328 0.20340 0.20018 -0.1181 0.0086 1.0000
18.250 1.1278 0.21326 0.21003 -0.1234 0.0087 1.0000
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