USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 200,000 Max Cl/Cd: 64.37 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27m2-il-200000.txt Download as CSV file: xf-usa27m2-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3183 0.09886 0.09566 -0.0368 0.9904 0.0614
-8.000 -0.3396 0.09300 0.08979 -0.0520 0.9787 0.0642
-7.750 -0.3304 0.08686 0.08364 -0.0563 0.9737 0.0651
-7.500 -0.3068 0.08443 0.08122 -0.0554 0.9721 0.0662
-7.250 -0.2919 0.08186 0.07866 -0.0559 0.9662 0.0676
-7.000 -0.2697 0.07799 0.07475 -0.0605 0.9604 0.0703
-6.750 -0.2692 0.06932 0.06580 -0.0728 0.9475 0.0763
-6.500 -0.2370 0.06655 0.06309 -0.0742 0.9450 0.0777
-6.250 -0.2174 0.06443 0.06097 -0.0742 0.9367 0.0797
-5.750 -0.1731 0.05578 0.05203 -0.0816 0.9217 0.0910
-5.500 -0.1399 0.05327 0.04948 -0.0842 0.9172 0.0951
-5.250 -0.1075 0.04851 0.04446 -0.0892 0.9141 0.1047
-5.000 -0.0930 0.04704 0.04299 -0.0874 0.9037 0.1079
-4.750 -0.0611 0.04350 0.03923 -0.0906 0.9003 0.1190
-4.500 -0.0242 0.04061 0.03610 -0.0940 0.8983 0.1323
-4.250 -0.0095 0.03930 0.03484 -0.0916 0.8875 0.1352
-4.000 0.0135 0.02774 0.02116 -0.0899 0.8835 0.0754
-3.750 0.0320 0.02441 0.01724 -0.0873 0.8740 0.0651
-3.500 0.0711 0.02242 0.01511 -0.0891 0.8701 0.0627
-3.250 0.1133 0.02058 0.01304 -0.0914 0.8671 0.0609
-3.000 0.1385 0.01953 0.01183 -0.0902 0.8567 0.0600
-2.750 0.1801 0.01828 0.01043 -0.0923 0.8516 0.0594
-2.500 0.2075 0.01748 0.00957 -0.0917 0.8407 0.0594
-2.250 0.2480 0.01658 0.00862 -0.0938 0.8341 0.0609
-2.000 0.2736 0.01601 0.00803 -0.0928 0.8210 0.0621
-1.750 0.3019 0.01543 0.00742 -0.0925 0.8082 0.0627
-1.500 0.3309 0.01490 0.00686 -0.0923 0.7948 0.0635
-1.250 0.3587 0.01447 0.00638 -0.0918 0.7799 0.0646
-1.000 0.3842 0.01402 0.00589 -0.0910 0.7636 0.0669
-0.750 0.4099 0.01374 0.00552 -0.0902 0.7462 0.0703
-0.500 0.4355 0.01353 0.00520 -0.0894 0.7279 0.0755
-0.250 0.4581 0.01297 0.00493 -0.0881 0.7093 0.1463
0.000 0.4815 0.01273 0.00496 -0.0870 0.6901 0.2683
0.250 0.5064 0.01274 0.00493 -0.0862 0.6707 0.3168
0.500 0.5290 0.01278 0.00491 -0.0850 0.6506 0.3494
0.750 0.5504 0.01280 0.00489 -0.0835 0.6308 0.3823
1.000 0.5691 0.01267 0.00484 -0.0817 0.6119 0.4353
1.250 0.7506 0.01262 0.00569 -0.1132 0.5717 1.0000
1.500 0.7698 0.01284 0.00574 -0.1115 0.5533 1.0000
1.750 0.7887 0.01305 0.00580 -0.1097 0.5360 1.0000
2.000 0.8074 0.01326 0.00586 -0.1079 0.5199 1.0000
2.250 0.8260 0.01347 0.00594 -0.1061 0.5051 1.0000
2.500 0.8450 0.01369 0.00605 -0.1044 0.4921 1.0000
2.750 0.8644 0.01394 0.00617 -0.1028 0.4813 1.0000
3.000 0.8841 0.01420 0.00630 -0.1012 0.4717 1.0000
3.250 0.9043 0.01445 0.00648 -0.0998 0.4630 1.0000
3.500 0.9248 0.01473 0.00665 -0.0984 0.4552 1.0000
3.750 0.9454 0.01500 0.00685 -0.0971 0.4478 1.0000
4.000 0.9655 0.01526 0.00706 -0.0956 0.4404 1.0000
4.250 0.9868 0.01557 0.00728 -0.0945 0.4338 1.0000
4.500 1.0066 0.01581 0.00752 -0.0930 0.4274 1.0000
4.750 1.0285 0.01612 0.00775 -0.0919 0.4221 1.0000
5.000 1.0501 0.01644 0.00804 -0.0908 0.4167 1.0000
5.250 1.0690 0.01668 0.00831 -0.0892 0.4107 1.0000
5.500 1.0905 0.01699 0.00856 -0.0881 0.4055 1.0000
5.750 1.1130 0.01734 0.00889 -0.0872 0.4008 1.0000
6.000 1.1314 0.01760 0.00920 -0.0855 0.3958 1.0000
6.250 1.1516 0.01789 0.00949 -0.0841 0.3909 1.0000
6.500 1.1765 0.01831 0.00980 -0.0838 0.3860 1.0000
6.750 1.1915 0.01853 0.01016 -0.0814 0.3810 1.0000
7.000 1.2096 0.01880 0.01046 -0.0797 0.3758 1.0000
7.250 1.2313 0.01915 0.01076 -0.0787 0.3709 1.0000
7.500 1.2492 0.01948 0.01117 -0.0770 0.3661 1.0000
7.750 1.2649 0.01975 0.01151 -0.0748 0.3608 1.0000
8.000 1.2831 0.02004 0.01178 -0.0731 0.3553 1.0000
8.250 1.2975 0.02034 0.01213 -0.0707 0.3491 1.0000
8.500 1.3077 0.02053 0.01237 -0.0675 0.3420 1.0000
8.750 1.3217 0.02082 0.01263 -0.0651 0.3349 1.0000
9.000 1.3263 0.02100 0.01293 -0.0608 0.3279 1.0000
9.250 1.3384 0.02129 0.01316 -0.0580 0.3212 1.0000
9.500 1.3451 0.02158 0.01358 -0.0544 0.3140 1.0000
9.750 1.3540 0.02189 0.01391 -0.0512 0.3064 1.0000
10.000 1.3616 0.02227 0.01438 -0.0480 0.2979 1.0000
10.250 1.3702 0.02269 0.01479 -0.0451 0.2896 1.0000
10.500 1.3789 0.02317 0.01539 -0.0423 0.2805 1.0000
10.750 1.3878 0.02376 0.01594 -0.0397 0.2724 1.0000
11.000 1.3967 0.02435 0.01668 -0.0373 0.2623 1.0000
11.250 1.4044 0.02506 0.01743 -0.0348 0.2519 1.0000
11.500 1.4108 0.02591 0.01826 -0.0323 0.2418 1.0000
11.750 1.4182 0.02681 0.01921 -0.0301 0.2305 1.0000
12.000 1.4253 0.02782 0.02025 -0.0280 0.2198 1.0000
12.250 1.4302 0.02901 0.02146 -0.0259 0.2092 1.0000
12.500 1.4324 0.03046 0.02288 -0.0237 0.1984 1.0000
12.750 1.4351 0.03199 0.02442 -0.0217 0.1882 1.0000
13.000 1.4373 0.03364 0.02609 -0.0198 0.1788 1.0000
13.250 1.4354 0.03569 0.02812 -0.0178 0.1694 1.0000
13.500 1.4351 0.03774 0.03021 -0.0162 0.1598 1.0000
13.750 1.4365 0.03977 0.03231 -0.0150 0.1508 1.0000
14.000 1.4341 0.04227 0.03483 -0.0137 0.1417 1.0000
14.250 1.4331 0.04478 0.03739 -0.0128 0.1290 1.0000
14.500 1.4303 0.04760 0.04023 -0.0121 0.1106 1.0000
14.750 1.4144 0.05197 0.04450 -0.0116 0.0889 1.0000
15.000 1.3932 0.05716 0.04960 -0.0113 0.0705 1.0000
15.250 1.3668 0.06318 0.05555 -0.0115 0.0476 1.0000
15.500 1.3443 0.06901 0.06137 -0.0119 0.0401 1.0000
15.750 1.3284 0.07420 0.06664 -0.0126 0.0373 1.0000
16.000 1.3141 0.07936 0.07191 -0.0135 0.0353 1.0000
16.250 1.3019 0.08438 0.07706 -0.0145 0.0340 1.0000
16.500 1.2899 0.08946 0.08228 -0.0156 0.0331 1.0000
16.750 1.2772 0.09473 0.08768 -0.0169 0.0323 1.0000
17.000 1.2637 0.10020 0.09329 -0.0184 0.0317 1.0000
17.250 1.2499 0.10583 0.09906 -0.0201 0.0311 1.0000
17.500 1.2357 0.11158 0.10494 -0.0219 0.0306 1.0000
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