WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WACO COOTIE AIRFOIL (cootie-il) Reynolds number: 100,000 Max Cl/Cd: 60.06 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cootie-il-100000.txt Download as CSV file: xf-cootie-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3200 0.10700 0.10253 -0.0300 1.0000 0.0675
-8.250 -0.3398 0.10727 0.10291 -0.0276 1.0000 0.0677
-8.000 -0.3547 0.10727 0.10300 -0.0279 1.0000 0.0679
-7.750 -0.3635 0.10684 0.10262 -0.0300 1.0000 0.0681
-7.500 -0.3625 0.10106 0.09691 -0.0250 1.0000 0.0689
-7.250 -0.3595 0.09689 0.09278 -0.0200 1.0000 0.0702
-7.000 -0.3618 0.09456 0.09050 -0.0179 1.0000 0.0714
-6.750 -0.3648 0.09252 0.08850 -0.0168 1.0000 0.0729
-6.500 -0.3671 0.09050 0.08653 -0.0165 1.0000 0.0746
-6.250 -0.3676 0.08845 0.08451 -0.0171 1.0000 0.0766
-6.000 -0.3068 0.08375 0.07957 -0.0399 0.9906 0.0818
-5.750 -0.2941 0.07853 0.07443 -0.0368 0.9861 0.0841
-5.500 -0.2628 0.07444 0.07027 -0.0419 0.9795 0.0887
-5.250 -0.1964 0.06983 0.06529 -0.0606 0.9713 0.0958
-5.000 -0.1795 0.06538 0.06092 -0.0602 0.9641 0.0978
-4.750 -0.1418 0.06163 0.05707 -0.0655 0.9581 0.1045
-4.500 -0.0978 0.05759 0.05279 -0.0740 0.9495 0.1114
-4.250 -0.0598 0.05404 0.04915 -0.0785 0.9438 0.1174
-4.000 -0.0160 0.05058 0.04540 -0.0854 0.9354 0.1255
-3.750 0.0333 0.04759 0.04209 -0.0922 0.9296 0.1384
-3.250 0.1055 0.04194 0.03626 -0.0988 0.9157 0.1611
-3.000 0.1566 0.03901 0.03308 -0.1050 0.9125 0.1836
-2.750 0.1845 0.03720 0.03121 -0.1061 0.9022 0.2021
-2.500 0.2281 0.03498 0.02894 -0.1100 0.8986 0.2483
-1.750 0.3750 0.02755 0.01930 -0.1188 0.8770 0.1061
-1.500 0.4155 0.02589 0.01732 -0.1204 0.8701 0.1041
-1.250 0.4480 0.02500 0.01611 -0.1205 0.8599 0.1077
-1.000 0.4865 0.02357 0.01456 -0.1217 0.8533 0.1134
-0.750 0.5140 0.02285 0.01373 -0.1211 0.8419 0.1189
-0.500 0.5449 0.02190 0.01274 -0.1209 0.8334 0.1300
-0.250 0.5744 0.02079 0.01172 -0.1206 0.8247 0.1622
0.000 0.5996 0.02018 0.01123 -0.1198 0.8142 0.2056
0.250 0.6313 0.01950 0.01067 -0.1198 0.8075 0.2490
0.500 0.6550 0.01866 0.01075 -0.1193 0.7960 0.5077
0.750 0.6815 0.01787 0.01055 -0.1179 0.7859 1.0000
1.000 0.7117 0.01772 0.01016 -0.1174 0.7781 1.0000
1.250 0.7366 0.01787 0.01018 -0.1166 0.7662 1.0000
1.500 0.7627 0.01796 0.01015 -0.1159 0.7552 1.0000
1.750 0.7911 0.01787 0.00994 -0.1153 0.7461 1.0000
2.000 0.8179 0.01788 0.00985 -0.1147 0.7351 1.0000
2.250 0.8436 0.01798 0.00989 -0.1140 0.7229 1.0000
2.500 0.8700 0.01804 0.00989 -0.1134 0.7113 1.0000
2.750 0.8973 0.01806 0.00985 -0.1128 0.7001 1.0000
3.000 0.9257 0.01800 0.00970 -0.1124 0.6892 1.0000
3.250 0.9519 0.01813 0.00979 -0.1117 0.6760 1.0000
3.500 0.9779 0.01832 0.00997 -0.1112 0.6625 1.0000
3.750 1.0039 0.01854 0.01017 -0.1106 0.6488 1.0000
4.000 1.0299 0.01880 0.01040 -0.1100 0.6349 1.0000
4.250 1.0557 0.01912 0.01070 -0.1095 0.6209 1.0000
4.500 1.0813 0.01948 0.01109 -0.1090 0.6069 1.0000
4.750 1.1066 0.01987 0.01147 -0.1084 0.5929 1.0000
5.000 1.1318 0.02023 0.01185 -0.1078 0.5786 1.0000
5.250 1.1566 0.02057 0.01220 -0.1072 0.5640 1.0000
5.500 1.1811 0.02086 0.01254 -0.1064 0.5491 1.0000
5.750 1.2053 0.02113 0.01284 -0.1056 0.5343 1.0000
6.000 1.2294 0.02141 0.01316 -0.1049 0.5199 1.0000
6.250 1.2534 0.02168 0.01351 -0.1041 0.5057 1.0000
6.500 1.2767 0.02194 0.01382 -0.1032 0.4909 1.0000
6.750 1.2987 0.02207 0.01401 -0.1020 0.4734 1.0000
7.000 1.3200 0.02207 0.01396 -0.1006 0.4530 1.0000
7.250 1.3390 0.02231 0.01429 -0.0990 0.4328 1.0000
7.500 1.3580 0.02261 0.01468 -0.0975 0.4131 1.0000
7.750 1.3761 0.02295 0.01502 -0.0958 0.3926 1.0000
8.000 1.3921 0.02341 0.01562 -0.0939 0.3708 1.0000
8.250 1.4065 0.02394 0.01617 -0.0918 0.3472 1.0000
8.500 1.4169 0.02460 0.01685 -0.0891 0.3176 1.0000
8.750 1.4236 0.02545 0.01775 -0.0860 0.2797 1.0000
9.000 1.4243 0.02672 0.01887 -0.0822 0.2218 1.0000
9.250 1.4087 0.02911 0.02067 -0.0766 0.1506 1.0000
9.500 1.3906 0.03229 0.02335 -0.0716 0.0993 1.0000
9.750 1.3760 0.03551 0.02639 -0.0675 0.0785 1.0000
10.000 1.3661 0.03852 0.02941 -0.0644 0.0677 1.0000
10.250 1.3583 0.04150 0.03242 -0.0620 0.0611 1.0000
10.500 1.3553 0.04420 0.03525 -0.0600 0.0562 1.0000
10.750 1.3524 0.04698 0.03813 -0.0583 0.0529 1.0000
11.000 1.3480 0.04999 0.04118 -0.0567 0.0505 1.0000
11.250 1.3467 0.05275 0.04399 -0.0550 0.0487 1.0000
11.500 1.3519 0.05499 0.04637 -0.0533 0.0468 1.0000
11.750 1.3599 0.05703 0.04849 -0.0516 0.0449 1.0000
12.000 1.3681 0.05910 0.05061 -0.0502 0.0429 1.0000
12.250 1.3783 0.06114 0.05261 -0.0487 0.0408 1.0000
12.500 1.3963 0.06313 0.05468 -0.0469 0.0392 1.0000
12.750 1.4125 0.06552 0.05731 -0.0454 0.0385 1.0000
13.000 1.4244 0.06850 0.06056 -0.0440 0.0382 1.0000
13.250 1.4289 0.07208 0.06447 -0.0429 0.0380 1.0000
13.500 1.4264 0.07615 0.06884 -0.0419 0.0380 1.0000
13.750 1.4188 0.08060 0.07360 -0.0414 0.0381 1.0000
14.000 1.4075 0.08539 0.07868 -0.0412 0.0383 1.0000
14.250 1.3936 0.09054 0.08411 -0.0415 0.0385 1.0000
14.500 1.3774 0.09603 0.08986 -0.0424 0.0387 1.0000
14.750 1.3599 0.10186 0.09593 -0.0438 0.0389 1.0000
15.000 1.3415 0.10808 0.10237 -0.0459 0.0392 1.0000
15.250 1.3229 0.11468 0.10918 -0.0486 0.0394 1.0000
15.500 1.3047 0.12167 0.11635 -0.0518 0.0397 1.0000
15.750 1.2882 0.12892 0.12379 -0.0552 0.0400 1.0000
16.000 1.2644 0.13733 0.13244 -0.0614 0.0404 1.0000
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Polar data table (+)
Polar graphs
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