GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 100,000 Max Cl/Cd: 41.75 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe290-il-100000.txt Download as CSV file: xf-goe290-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 290 (MVA 290) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2855 0.09767 0.09294 -0.0363 1.0000 0.1994
-8.750 -0.5646 0.06146 0.05637 -0.0601 0.9851 0.1196
-8.500 -0.5415 0.05470 0.04930 -0.0660 0.9738 0.1147
-8.250 -0.5262 0.04749 0.04146 -0.0713 0.9601 0.1119
-8.000 -0.4966 0.04272 0.03614 -0.0756 0.9477 0.1122
-7.750 -0.4602 0.03878 0.03168 -0.0796 0.9371 0.1130
-7.500 -0.4265 0.03572 0.02815 -0.0819 0.9222 0.1140
-7.250 -0.3946 0.03338 0.02535 -0.0832 0.9053 0.1161
-7.000 -0.3643 0.03147 0.02296 -0.0838 0.8879 0.1187
-6.750 -0.3333 0.02954 0.02099 -0.0844 0.8704 0.1218
-6.500 -0.3041 0.02818 0.01946 -0.0843 0.8524 0.1249
-6.250 -0.2769 0.02710 0.01810 -0.0837 0.8343 0.1291
-6.000 -0.2509 0.02599 0.01676 -0.0830 0.8167 0.1333
-5.750 -0.2248 0.02506 0.01583 -0.0825 0.8002 0.1380
-5.500 -0.1988 0.02441 0.01499 -0.0820 0.7858 0.1439
-5.250 -0.1724 0.02354 0.01408 -0.0815 0.7740 0.1503
-5.000 -0.1466 0.02292 0.01343 -0.0810 0.7616 0.1581
-4.750 -0.1214 0.02223 0.01277 -0.0805 0.7508 0.1670
-4.500 -0.0957 0.02165 0.01216 -0.0799 0.7412 0.1788
-4.250 -0.0711 0.02108 0.01171 -0.0794 0.7323 0.1949
-4.000 -0.0470 0.02048 0.01137 -0.0789 0.7241 0.2217
-3.750 -0.0230 0.02002 0.01136 -0.0781 0.7176 0.3039
-3.500 0.0002 0.02025 0.01175 -0.0772 0.7091 0.3854
-3.250 0.0257 0.02040 0.01185 -0.0764 0.7026 0.4244
-3.000 0.0516 0.02058 0.01195 -0.0759 0.6962 0.4525
-2.750 0.0772 0.02068 0.01210 -0.0755 0.6896 0.4749
-2.500 0.1041 0.02071 0.01210 -0.0751 0.6843 0.4955
-2.250 0.1311 0.02078 0.01213 -0.0747 0.6794 0.5151
-2.000 0.1564 0.02091 0.01235 -0.0744 0.6729 0.5350
-1.750 0.1824 0.02095 0.01245 -0.0739 0.6675 0.5580
-1.500 0.2091 0.02098 0.01250 -0.0734 0.6633 0.5825
-1.250 0.2340 0.02116 0.01279 -0.0729 0.6587 0.6078
-1.000 0.2587 0.02134 0.01308 -0.0725 0.6533 0.6346
-0.750 0.2844 0.02135 0.01322 -0.0718 0.6486 0.6610
-0.500 0.3117 0.02131 0.01324 -0.0714 0.6446 0.6917
-0.250 0.3355 0.02148 0.01361 -0.0705 0.6402 0.7308
0.000 0.3569 0.02170 0.01415 -0.0690 0.6353 0.7910
0.250 0.3887 0.02183 0.01448 -0.0686 0.6303 0.8823
0.500 0.4585 0.02189 0.01435 -0.0755 0.6248 0.9627
0.750 0.5373 0.02232 0.01468 -0.0863 0.6159 1.0000
1.000 0.5537 0.02251 0.01472 -0.0850 0.6105 1.0000
1.250 0.5766 0.02259 0.01458 -0.0840 0.6057 1.0000
1.500 0.5914 0.02319 0.01519 -0.0825 0.5986 1.0000
1.750 0.6127 0.02343 0.01532 -0.0814 0.5921 1.0000
2.000 0.6392 0.02347 0.01516 -0.0808 0.5869 1.0000
2.250 0.6554 0.02413 0.01585 -0.0793 0.5800 1.0000
2.500 0.6768 0.02455 0.01622 -0.0784 0.5741 1.0000
2.750 0.7027 0.02477 0.01633 -0.0779 0.5696 1.0000
3.000 0.7265 0.02525 0.01674 -0.0773 0.5650 1.0000
3.250 0.7420 0.02611 0.01769 -0.0759 0.5581 1.0000
3.500 0.7673 0.02641 0.01793 -0.0754 0.5528 1.0000
3.750 0.7971 0.02652 0.01791 -0.0753 0.5486 1.0000
4.000 0.8106 0.02757 0.01908 -0.0737 0.5412 1.0000
4.250 0.8344 0.02796 0.01946 -0.0731 0.5349 1.0000
4.500 0.8654 0.02794 0.01932 -0.0732 0.5302 1.0000
4.750 0.8799 0.02892 0.02041 -0.0716 0.5223 1.0000
5.000 0.9046 0.02919 0.02066 -0.0710 0.5153 1.0000
5.250 0.9386 0.02897 0.02031 -0.0714 0.5105 1.0000
5.500 0.9489 0.03007 0.02157 -0.0693 0.5008 1.0000
5.750 0.9788 0.02996 0.02140 -0.0692 0.4944 1.0000
6.000 1.0045 0.03023 0.02164 -0.0687 0.4877 1.0000
6.250 1.0215 0.03082 0.02232 -0.0673 0.4784 1.0000
6.500 1.0578 0.03041 0.02177 -0.0679 0.4732 1.0000
6.750 1.0664 0.03146 0.02300 -0.0655 0.4623 1.0000
7.000 1.1006 0.03104 0.02248 -0.0659 0.4562 1.0000
7.250 1.1130 0.03189 0.02345 -0.0639 0.4464 1.0000
7.500 1.1436 0.03160 0.02310 -0.0639 0.4395 1.0000
7.750 1.1611 0.03214 0.02369 -0.0625 0.4311 1.0000
8.000 1.1859 0.03208 0.02364 -0.0618 0.4232 1.0000
8.250 1.2127 0.03195 0.02346 -0.0614 0.4162 1.0000
8.500 1.2279 0.03237 0.02395 -0.0596 0.4074 1.0000
8.750 1.2655 0.03152 0.02296 -0.0604 0.4014 1.0000
9.000 1.2679 0.03269 0.02433 -0.0573 0.3924 1.0000
9.250 1.3056 0.03186 0.02334 -0.0580 0.3866 1.0000
9.500 1.3067 0.03318 0.02487 -0.0549 0.3788 1.0000
9.750 1.3332 0.03295 0.02459 -0.0544 0.3724 1.0000
10.000 1.3490 0.03340 0.02508 -0.0529 0.3659 1.0000
10.250 1.3575 0.03414 0.02592 -0.0505 0.3591 1.0000
10.500 1.3965 0.03345 0.02507 -0.0516 0.3536 1.0000
10.750 1.3839 0.03529 0.02717 -0.0469 0.3479 1.0000
11.000 1.3937 0.03604 0.02798 -0.0448 0.3425 1.0000
11.250 1.4275 0.03558 0.02742 -0.0452 0.3366 1.0000
11.500 1.4103 0.03780 0.02988 -0.0407 0.3316 1.0000
11.750 1.4238 0.03834 0.03044 -0.0393 0.3256 1.0000
12.000 1.4462 0.03851 0.03058 -0.0386 0.3201 1.0000
12.250 1.4277 0.04127 0.03357 -0.0352 0.3152 1.0000
12.500 1.4445 0.04172 0.03404 -0.0343 0.3093 1.0000
12.750 1.4560 0.04260 0.03494 -0.0331 0.3037 1.0000
13.000 1.4354 0.04614 0.03870 -0.0309 0.2990 1.0000
13.250 1.4614 0.04579 0.03830 -0.0304 0.2924 1.0000
13.500 1.4563 0.04827 0.04090 -0.0291 0.2874 1.0000
13.750 1.4313 0.05286 0.04571 -0.0280 0.2828 1.0000
14.000 1.4789 0.05019 0.04285 -0.0274 0.2745 1.0000
14.250 1.4415 0.05625 0.04921 -0.0267 0.2708 1.0000
14.500 1.4142 0.06176 0.05492 -0.0266 0.2659 1.0000
14.750 1.4546 0.05934 0.05237 -0.0256 0.2577 1.0000
15.000 1.4067 0.06762 0.06094 -0.0264 0.2539 1.0000
15.250 1.4525 0.06414 0.05728 -0.0249 0.2435 1.0000
15.500 1.4014 0.07329 0.06674 -0.0265 0.2399 1.0000
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Polar data table (+)
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