WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WACO COOTIE AIRFOIL (cootie-il) Reynolds number: 100,000 Max Cl/Cd: 62.82 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cootie-il-100000-n5.txt Download as CSV file: xf-cootie-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2839 0.10293 0.09834 -0.0325 1.0000 0.0451
-8.500 -0.2937 0.10180 0.09729 -0.0302 1.0000 0.0464
-8.250 -0.3026 0.10060 0.09618 -0.0292 0.9981 0.0480
-8.000 -0.2856 0.09755 0.09313 -0.0414 0.9858 0.0497
-7.750 -0.2612 0.09337 0.08890 -0.0532 0.9764 0.0500
-7.500 -0.2497 0.08800 0.08357 -0.0484 0.9747 0.0512
-7.250 -0.2322 0.08437 0.07992 -0.0499 0.9686 0.0534
-7.000 -0.1999 0.08090 0.07636 -0.0626 0.9598 0.0602
-6.750 -0.1688 0.07592 0.07126 -0.0732 0.9524 0.0613
-6.500 -0.1543 0.07174 0.06710 -0.0717 0.9480 0.0626
-6.250 -0.1339 0.06829 0.06362 -0.0739 0.9408 0.0646
-6.000 -0.1034 0.06450 0.05973 -0.0796 0.9358 0.0684
-5.750 -0.0502 0.06106 0.05579 -0.0946 0.9256 0.0731
-5.500 -0.0187 0.05660 0.05115 -0.0988 0.9209 0.0731
-5.250 -0.0108 0.05117 0.04589 -0.0964 0.9134 0.0578
-5.000 0.0227 0.04709 0.04158 -0.1010 0.9076 0.0560
-4.500 0.0986 0.03676 0.03023 -0.1106 0.8938 0.0499
-4.250 0.1293 0.03375 0.02689 -0.1124 0.8872 0.0499
-4.000 0.1557 0.03231 0.02539 -0.1132 0.8794 0.0519
-3.750 0.1854 0.03047 0.02329 -0.1142 0.8722 0.0534
-3.500 0.2169 0.02771 0.02006 -0.1153 0.8646 0.0525
-3.250 0.2477 0.02546 0.01736 -0.1160 0.8572 0.0523
-3.000 0.2775 0.02376 0.01529 -0.1164 0.8493 0.0526
-2.750 0.3062 0.02244 0.01366 -0.1165 0.8408 0.0532
-2.500 0.3358 0.02132 0.01226 -0.1166 0.8331 0.0543
-2.250 0.3630 0.02061 0.01136 -0.1163 0.8234 0.0574
-2.000 0.3925 0.01966 0.01012 -0.1163 0.8160 0.0599
-1.750 0.4193 0.01888 0.00921 -0.1158 0.8057 0.0610
-1.500 0.4463 0.01836 0.00866 -0.1155 0.7960 0.0629
-1.250 0.4743 0.01786 0.00810 -0.1152 0.7868 0.0657
-1.000 0.5004 0.01742 0.00760 -0.1146 0.7741 0.0701
-0.750 0.5267 0.01705 0.00720 -0.1140 0.7615 0.0769
-0.500 0.5532 0.01677 0.00687 -0.1134 0.7495 0.0906
-0.250 0.5801 0.01660 0.00662 -0.1130 0.7385 0.1095
0.000 0.6074 0.01648 0.00644 -0.1127 0.7279 0.1308
0.250 0.6341 0.01637 0.00633 -0.1125 0.7164 0.1520
0.500 0.6612 0.01627 0.00618 -0.1122 0.7058 0.1632
0.750 0.6886 0.01613 0.00604 -0.1120 0.6957 0.1856
1.000 0.7157 0.01588 0.00602 -0.1120 0.6850 0.2462
1.500 0.7667 0.01460 0.00596 -0.1106 0.6643 1.0000
1.750 0.7937 0.01475 0.00596 -0.1102 0.6541 1.0000
2.000 0.8202 0.01494 0.00605 -0.1099 0.6430 1.0000
2.250 0.8467 0.01514 0.00614 -0.1096 0.6323 1.0000
2.500 0.8735 0.01533 0.00623 -0.1093 0.6223 1.0000
2.750 0.8996 0.01557 0.00643 -0.1090 0.6111 1.0000
3.000 0.9256 0.01581 0.00663 -0.1087 0.5998 1.0000
3.250 0.9517 0.01606 0.00683 -0.1084 0.5889 1.0000
3.500 0.9777 0.01632 0.00705 -0.1080 0.5780 1.0000
3.750 1.0030 0.01659 0.00735 -0.1077 0.5659 1.0000
4.000 1.0283 0.01687 0.00765 -0.1073 0.5539 1.0000
4.250 1.0536 0.01715 0.00796 -0.1069 0.5419 1.0000
4.500 1.0787 0.01744 0.00826 -0.1065 0.5301 1.0000
4.750 1.1035 0.01774 0.00858 -0.1060 0.5178 1.0000
5.000 1.1277 0.01805 0.00895 -0.1054 0.5036 1.0000
5.250 1.1515 0.01837 0.00930 -0.1048 0.4889 1.0000
5.500 1.1750 0.01871 0.00968 -0.1041 0.4743 1.0000
5.750 1.1980 0.01907 0.01007 -0.1034 0.4594 1.0000
6.000 1.2206 0.01946 0.01052 -0.1026 0.4442 1.0000
6.250 1.2426 0.01988 0.01096 -0.1017 0.4286 1.0000
6.500 1.2628 0.02033 0.01143 -0.1005 0.4078 1.0000
6.750 1.2812 0.02086 0.01190 -0.0991 0.3844 1.0000
7.000 1.2994 0.02142 0.01247 -0.0977 0.3617 1.0000
7.250 1.3167 0.02207 0.01312 -0.0962 0.3400 1.0000
7.500 1.3319 0.02279 0.01381 -0.0944 0.3126 1.0000
7.750 1.3451 0.02364 0.01459 -0.0924 0.2804 1.0000
8.000 1.3581 0.02452 0.01543 -0.0905 0.2452 1.0000
8.250 1.3684 0.02559 0.01639 -0.0882 0.2056 1.0000
8.500 1.3687 0.02729 0.01773 -0.0847 0.1541 1.0000
9.000 1.3600 0.03156 0.02143 -0.0772 0.0749 1.0000
9.250 1.3602 0.03354 0.02333 -0.0744 0.0450 1.0000
9.750 1.3595 0.03783 0.02759 -0.0695 0.0280 1.0000
10.000 1.3593 0.04010 0.02996 -0.0675 0.0258 1.0000
10.250 1.3577 0.04259 0.03257 -0.0656 0.0242 1.0000
10.500 1.3570 0.04511 0.03528 -0.0640 0.0230 1.0000
10.750 1.3550 0.04786 0.03822 -0.0627 0.0219 1.0000
11.000 1.3514 0.05089 0.04144 -0.0616 0.0210 1.0000
11.250 1.3468 0.05417 0.04489 -0.0607 0.0204 1.0000
11.500 1.3414 0.05767 0.04861 -0.0601 0.0199 1.0000
11.750 1.3353 0.06138 0.05250 -0.0597 0.0196 1.0000
12.000 1.3286 0.06528 0.05656 -0.0595 0.0192 1.0000
12.250 1.3216 0.06928 0.06071 -0.0594 0.0189 1.0000
12.500 1.3152 0.07328 0.06486 -0.0594 0.0186 1.0000
12.750 1.3098 0.07717 0.06888 -0.0593 0.0183 1.0000
13.000 1.3058 0.08078 0.07259 -0.0590 0.0180 1.0000
13.250 1.3055 0.08393 0.07585 -0.0585 0.0176 1.0000
13.500 1.3066 0.08706 0.07914 -0.0584 0.0172 1.0000
13.750 1.3078 0.09023 0.08248 -0.0583 0.0168 1.0000
14.000 1.3087 0.09347 0.08588 -0.0583 0.0163 1.0000
14.250 1.3093 0.09680 0.08938 -0.0583 0.0159 1.0000
14.500 1.3099 0.10019 0.09294 -0.0584 0.0156 1.0000
14.750 1.3101 0.10376 0.09673 -0.0587 0.0154 1.0000
15.000 1.3087 0.10769 0.10086 -0.0593 0.0152 1.0000
15.250 1.3058 0.11197 0.10534 -0.0603 0.0151 1.0000
15.500 1.3013 0.11669 0.11028 -0.0618 0.0150 1.0000
15.750 1.2951 0.12189 0.11569 -0.0637 0.0149 1.0000
16.000 1.2875 0.12754 0.12156 -0.0663 0.0149 1.0000
16.250 1.2785 0.13373 0.12797 -0.0694 0.0149 1.0000
16.500 1.2682 0.14047 0.13493 -0.0731 0.0149 1.0000
16.750 1.2565 0.14781 0.14249 -0.0775 0.0149 1.0000
17.000 1.2436 0.15589 0.15077 -0.0825 0.0150 1.0000
17.250 1.2293 0.16485 0.15994 -0.0884 0.0151 1.0000
17.500 1.2134 0.17502 0.17028 -0.0951 0.0153 1.0000
17.750 1.1956 0.18683 0.18224 -0.1029 0.0156 1.0000
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