WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WACO COOTIE AIRFOIL (cootie-il) Reynolds number: 200,000 Max Cl/Cd: 84.02 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cootie-il-200000.txt Download as CSV file: xf-cootie-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WACO COOTIE 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2939 0.10362 0.10030 -0.0344 1.0000 0.0357
-8.750 -0.3144 0.10374 0.10052 -0.0305 1.0000 0.0358
-8.500 -0.3377 0.10400 0.10088 -0.0257 1.0000 0.0359
-8.250 -0.3446 0.10265 0.09960 -0.0281 0.9974 0.0360
-7.750 -0.3085 0.09174 0.08866 -0.0341 0.9908 0.0373
-7.500 -0.2876 0.08780 0.08471 -0.0367 0.9871 0.0386
-7.250 -0.2612 0.08373 0.08061 -0.0428 0.9835 0.0410
-7.000 -0.2262 0.07942 0.07623 -0.0565 0.9749 0.0452
-6.750 -0.1866 0.07285 0.06956 -0.0704 0.9707 0.0464
-6.500 -0.1738 0.06950 0.06623 -0.0685 0.9653 0.0475
-6.250 -0.1465 0.06602 0.06271 -0.0721 0.9610 0.0499
-5.750 -0.0661 0.05653 0.05297 -0.0906 0.9514 0.0582
-5.500 -0.0388 0.05355 0.04996 -0.0930 0.9466 0.0607
-5.250 0.0242 0.04902 0.04491 -0.1065 0.9426 0.0687
-5.000 0.0402 0.04548 0.04147 -0.1061 0.9349 0.0699
-4.750 0.0667 0.04304 0.03903 -0.1074 0.9297 0.0731
-4.500 0.1140 0.04060 0.03597 -0.1135 0.9223 0.0817
-4.250 0.1358 0.03692 0.03239 -0.1141 0.9154 0.0832
-4.000 0.1601 0.03474 0.03016 -0.1145 0.9077 0.0854
-3.750 0.1884 0.03273 0.02799 -0.1153 0.8998 0.0898
-3.500 0.2209 0.03053 0.02536 -0.1167 0.8908 0.0969
-3.250 0.2460 0.02851 0.02330 -0.1168 0.8833 0.0993
-3.000 0.2721 0.02695 0.02157 -0.1167 0.8728 0.1029
-2.750 0.3114 0.02182 0.01538 -0.1172 0.8665 0.0700
-2.500 0.3386 0.02009 0.01339 -0.1167 0.8558 0.0658
-2.250 0.3659 0.01872 0.01171 -0.1161 0.8449 0.0664
-2.000 0.3933 0.01731 0.01001 -0.1154 0.8345 0.0657
-1.750 0.4205 0.01612 0.00855 -0.1148 0.8235 0.0654
-1.500 0.4475 0.01524 0.00748 -0.1142 0.8119 0.0663
-1.250 0.4748 0.01458 0.00669 -0.1137 0.8018 0.0678
-1.000 0.5021 0.01392 0.00598 -0.1132 0.7928 0.0709
-0.750 0.5291 0.01367 0.00573 -0.1129 0.7812 0.0766
-0.500 0.5564 0.01337 0.00543 -0.1126 0.7707 0.0855
-0.250 0.5840 0.01304 0.00508 -0.1122 0.7612 0.1067
0.000 0.6112 0.01279 0.00485 -0.1120 0.7502 0.1333
0.250 0.6383 0.01268 0.00472 -0.1118 0.7393 0.1501
0.500 0.6656 0.01253 0.00457 -0.1117 0.7290 0.1617
0.750 0.6930 0.01241 0.00443 -0.1115 0.7190 0.1794
1.000 0.7201 0.01230 0.00438 -0.1114 0.7074 0.1960
1.250 0.7430 0.01057 0.00441 -0.1103 0.6970 1.0000
1.500 0.7706 0.01070 0.00435 -0.1100 0.6869 1.0000
1.750 0.7978 0.01084 0.00434 -0.1097 0.6760 1.0000
2.000 0.8247 0.01100 0.00440 -0.1095 0.6643 1.0000
2.250 0.8516 0.01118 0.00447 -0.1093 0.6528 1.0000
2.500 0.8786 0.01138 0.00458 -0.1090 0.6419 1.0000
2.750 0.9055 0.01159 0.00469 -0.1088 0.6309 1.0000
3.000 0.9319 0.01180 0.00487 -0.1086 0.6185 1.0000
3.250 0.9582 0.01202 0.00505 -0.1083 0.6059 1.0000
3.500 0.9845 0.01226 0.00525 -0.1081 0.5934 1.0000
3.750 1.0105 0.01248 0.00544 -0.1077 0.5800 1.0000
4.000 1.0361 0.01269 0.00562 -0.1074 0.5654 1.0000
4.250 1.0615 0.01290 0.00581 -0.1069 0.5499 1.0000
4.500 1.0867 0.01311 0.00601 -0.1065 0.5344 1.0000
4.750 1.1116 0.01332 0.00620 -0.1060 0.5177 1.0000
5.000 1.1362 0.01355 0.00641 -0.1055 0.5009 1.0000
5.250 1.1608 0.01382 0.00667 -0.1050 0.4850 1.0000
5.500 1.1847 0.01410 0.00692 -0.1043 0.4679 1.0000
5.750 1.2080 0.01440 0.00720 -0.1037 0.4489 1.0000
6.000 1.2306 0.01473 0.00749 -0.1029 0.4279 1.0000
6.250 1.2525 0.01513 0.00783 -0.1020 0.4078 1.0000
6.500 1.2750 0.01551 0.00823 -0.1012 0.3898 1.0000
6.750 1.2966 0.01593 0.00865 -0.1004 0.3703 1.0000
7.000 1.3167 0.01645 0.00910 -0.0993 0.3492 1.0000
7.250 1.3363 0.01695 0.00961 -0.0981 0.3239 1.0000
7.500 1.3558 0.01750 0.01014 -0.0970 0.3012 1.0000
7.750 1.3736 0.01813 0.01072 -0.0956 0.2701 1.0000
8.000 1.3852 0.01917 0.01148 -0.0933 0.2108 1.0000
8.250 1.3834 0.02129 0.01296 -0.0894 0.1242 1.0000
8.500 1.3825 0.02326 0.01455 -0.0856 0.0764 1.0000
8.750 1.3842 0.02479 0.01596 -0.0819 0.0477 1.0000
9.000 1.3882 0.02626 0.01736 -0.0788 0.0362 1.0000
9.250 1.3926 0.02778 0.01892 -0.0759 0.0322 1.0000
9.500 1.3980 0.02928 0.02055 -0.0735 0.0302 1.0000
9.750 1.4025 0.03092 0.02232 -0.0712 0.0285 1.0000
10.000 1.4049 0.03279 0.02432 -0.0689 0.0270 1.0000
10.250 1.4039 0.03506 0.02669 -0.0667 0.0258 1.0000
10.500 1.4002 0.03768 0.02943 -0.0646 0.0251 1.0000
10.750 1.3950 0.04058 0.03245 -0.0625 0.0246 1.0000
11.000 1.3942 0.04316 0.03517 -0.0609 0.0243 1.0000
11.250 1.3944 0.04574 0.03787 -0.0595 0.0240 1.0000
11.500 1.3949 0.04833 0.04058 -0.0581 0.0237 1.0000
11.750 1.3963 0.05088 0.04324 -0.0568 0.0235 1.0000
12.000 1.3990 0.05335 0.04581 -0.0554 0.0232 1.0000
12.250 1.4034 0.05568 0.04825 -0.0539 0.0230 1.0000
12.500 1.4091 0.05794 0.05062 -0.0525 0.0226 1.0000
12.750 1.4150 0.06024 0.05304 -0.0513 0.0221 1.0000
13.000 1.4205 0.06261 0.05555 -0.0502 0.0216 1.0000
13.250 1.4253 0.06513 0.05820 -0.0491 0.0210 1.0000
13.500 1.4308 0.06777 0.06100 -0.0479 0.0209 1.0000
13.750 1.4346 0.07073 0.06417 -0.0469 0.0209 1.0000
14.000 1.4342 0.07424 0.06792 -0.0461 0.0210 1.0000
14.250 1.4301 0.07826 0.07222 -0.0456 0.0212 1.0000
14.500 1.4221 0.08286 0.07711 -0.0455 0.0214 1.0000
14.750 1.4106 0.08800 0.08253 -0.0459 0.0217 1.0000
15.000 1.3963 0.09364 0.08845 -0.0470 0.0220 1.0000
15.250 1.3803 0.09973 0.09480 -0.0486 0.0223 1.0000
15.500 1.3633 0.10624 0.10155 -0.0509 0.0226 1.0000
15.750 1.3453 0.11315 0.10869 -0.0538 0.0229 1.0000
16.000 1.3268 0.12049 0.11624 -0.0573 0.0232 1.0000
16.250 1.3081 0.12829 0.12423 -0.0616 0.0234 1.0000
16.500 1.2891 0.13659 0.13272 -0.0664 0.0237 1.0000
16.750 1.2700 0.14540 0.14169 -0.0719 0.0240 1.0000
17.000 1.2589 0.15254 0.14892 -0.0750 0.0246 1.0000
17.250 1.2462 0.16088 0.15743 -0.0813 0.0249 1.0000
17.500 1.1969 0.18337 0.18022 -0.0980 0.0259 1.0000
17.750 0.9012 0.16754 0.16461 -0.0680 0.0263 1.0000
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