WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WACO COOTIE AIRFOIL (cootie-il) Reynolds number: 500,000 Max Cl/Cd: 107.56 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cootie-il-500000-n5.txt Download as CSV file: xf-cootie-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2733 0.09533 0.09305 -0.0424 0.9426 0.0094
-9.250 -0.2715 0.09067 0.08835 -0.0447 0.9246 0.0097
-9.000 -0.2681 0.08698 0.08462 -0.0465 0.9112 0.0100
-8.750 -0.2590 0.08484 0.08244 -0.0477 0.9009 0.0103
-8.500 -0.2496 0.08270 0.08026 -0.0490 0.8917 0.0106
-8.250 -0.2416 0.08005 0.07760 -0.0510 0.8833 0.0111
-7.750 -0.2184 0.07180 0.06928 -0.0601 0.8683 0.0121
-7.250 -0.1840 0.06076 0.05811 -0.0740 0.8550 0.0136
-7.000 -0.1626 0.05879 0.05609 -0.0765 0.8491 0.0141
-6.750 -0.1397 0.05567 0.05290 -0.0805 0.8434 0.0149
-6.500 -0.1065 0.04336 0.04030 -0.0944 0.8372 0.0174
-6.000 -0.0563 0.04068 0.03747 -0.0974 0.8258 0.0185
-5.750 -0.0288 0.03788 0.03453 -0.0999 0.8196 0.0194
-5.500 0.0076 0.02058 0.01601 -0.1092 0.8155 0.0233
-5.250 0.0346 0.01884 0.01404 -0.1098 0.8090 0.0239
-5.000 0.0619 0.01776 0.01276 -0.1102 0.8026 0.0246
-4.750 0.0896 0.01694 0.01179 -0.1105 0.7955 0.0254
-4.500 0.1174 0.01569 0.01026 -0.1107 0.7882 0.0261
-4.250 0.1455 0.01456 0.00887 -0.1110 0.7804 0.0265
-4.000 0.1735 0.01368 0.00774 -0.1111 0.7719 0.0269
-3.750 0.2017 0.01294 0.00682 -0.1112 0.7620 0.0272
-3.500 0.2297 0.01238 0.00608 -0.1113 0.7499 0.0277
-3.250 0.2576 0.01193 0.00546 -0.1112 0.7339 0.0283
-3.000 0.2850 0.01150 0.00484 -0.1111 0.7129 0.0286
-2.750 0.3124 0.01115 0.00430 -0.1110 0.6896 0.0288
-2.500 0.3399 0.01089 0.00386 -0.1108 0.6706 0.0292
-2.250 0.3676 0.01066 0.00351 -0.1108 0.6567 0.0295
-2.000 0.3955 0.01048 0.00323 -0.1108 0.6452 0.0298
-1.750 0.4233 0.01034 0.00300 -0.1108 0.6347 0.0301
-1.500 0.4512 0.01014 0.00273 -0.1109 0.6254 0.0305
-1.250 0.4793 0.00995 0.00249 -0.1109 0.6174 0.0310
-1.000 0.5073 0.00985 0.00232 -0.1110 0.6092 0.0316
-0.750 0.5354 0.00976 0.00220 -0.1111 0.6012 0.0323
-0.500 0.5634 0.00972 0.00211 -0.1111 0.5936 0.0335
-0.250 0.5916 0.00967 0.00204 -0.1113 0.5866 0.0346
0.000 0.6196 0.00966 0.00200 -0.1113 0.5794 0.0352
0.250 0.6477 0.00965 0.00196 -0.1114 0.5720 0.0362
0.500 0.6756 0.00966 0.00195 -0.1115 0.5639 0.0376
1.000 0.7314 0.00965 0.00203 -0.1117 0.5478 0.0764
1.250 0.7594 0.00969 0.00209 -0.1118 0.5396 0.0879
1.500 0.7870 0.00975 0.00215 -0.1118 0.5311 0.0950
1.750 0.8146 0.00982 0.00222 -0.1119 0.5210 0.1004
2.000 0.8421 0.00989 0.00229 -0.1119 0.5094 0.1067
2.250 0.8691 0.00999 0.00238 -0.1119 0.4936 0.1195
2.500 0.8959 0.01009 0.00250 -0.1119 0.4767 0.1399
2.750 0.9229 0.00980 0.00272 -0.1123 0.4623 0.4243
3.250 0.9702 0.00902 0.00300 -0.1108 0.4336 1.0000
3.500 0.9959 0.00930 0.00316 -0.1106 0.4133 1.0000
3.750 1.0216 0.00958 0.00335 -0.1104 0.3930 1.0000
4.000 1.0474 0.00986 0.00356 -0.1102 0.3764 1.0000
4.250 1.0728 0.01015 0.00377 -0.1100 0.3596 1.0000
4.500 1.0974 0.01053 0.00403 -0.1096 0.3385 1.0000
4.750 1.1222 0.01088 0.00429 -0.1093 0.3189 1.0000
5.000 1.1468 0.01124 0.00457 -0.1090 0.2999 1.0000
5.250 1.1712 0.01160 0.00486 -0.1087 0.2812 1.0000
5.500 1.1945 0.01206 0.00518 -0.1082 0.2530 1.0000
5.750 1.2156 0.01273 0.00562 -0.1074 0.2093 1.0000
6.000 1.2320 0.01384 0.00636 -0.1059 0.1464 1.0000
6.250 1.2456 0.01518 0.00730 -0.1041 0.0803 1.0000
6.500 1.2655 0.01587 0.00788 -0.1030 0.0600 1.0000
6.750 1.2801 0.01700 0.00876 -0.1012 0.0190 1.0000
7.000 1.3004 0.01757 0.00938 -0.1002 0.0150 1.0000
7.250 1.3199 0.01818 0.01005 -0.0991 0.0126 1.0000
7.500 1.3397 0.01872 0.01066 -0.0980 0.0116 1.0000
7.750 1.3588 0.01928 0.01129 -0.0968 0.0109 1.0000
8.000 1.3764 0.01990 0.01199 -0.0954 0.0101 1.0000
8.250 1.3923 0.02058 0.01275 -0.0938 0.0094 1.0000
8.500 1.4037 0.02139 0.01363 -0.0914 0.0087 1.0000
8.750 1.4131 0.02236 0.01468 -0.0887 0.0081 1.0000
9.000 1.4252 0.02319 0.01560 -0.0867 0.0079 1.0000
9.250 1.4362 0.02414 0.01663 -0.0846 0.0075 1.0000
9.500 1.4458 0.02523 0.01781 -0.0826 0.0072 1.0000
9.750 1.4545 0.02643 0.01910 -0.0805 0.0069 1.0000
10.000 1.4623 0.02776 0.02053 -0.0786 0.0067 1.0000
10.250 1.4692 0.02921 0.02206 -0.0767 0.0064 1.0000
10.500 1.4754 0.03078 0.02371 -0.0750 0.0062 1.0000
10.750 1.4801 0.03253 0.02555 -0.0733 0.0060 1.0000
11.000 1.4803 0.03477 0.02788 -0.0715 0.0058 1.0000
11.250 1.4791 0.03724 0.03045 -0.0697 0.0056 1.0000
11.500 1.4834 0.03926 0.03258 -0.0686 0.0055 1.0000
11.750 1.4863 0.04150 0.03493 -0.0675 0.0053 1.0000
12.000 1.4873 0.04401 0.03756 -0.0665 0.0052 1.0000
12.250 1.4865 0.04680 0.04046 -0.0656 0.0050 1.0000
12.500 1.4850 0.04977 0.04356 -0.0649 0.0049 1.0000
12.750 1.4832 0.05286 0.04677 -0.0643 0.0048 1.0000
13.000 1.4810 0.05608 0.05011 -0.0639 0.0047 1.0000
13.250 1.4786 0.05944 0.05358 -0.0637 0.0046 1.0000
13.500 1.4761 0.06291 0.05716 -0.0637 0.0045 1.0000
13.750 1.4728 0.06652 0.06088 -0.0637 0.0044 1.0000
14.000 1.4695 0.07021 0.06467 -0.0639 0.0044 1.0000
14.250 1.4663 0.07397 0.06854 -0.0642 0.0043 1.0000
14.500 1.4623 0.07791 0.07259 -0.0646 0.0042 1.0000
14.750 1.4581 0.08192 0.07670 -0.0652 0.0042 1.0000
15.000 1.4535 0.08605 0.08094 -0.0659 0.0041 1.0000
15.250 1.4485 0.09032 0.08531 -0.0667 0.0041 1.0000
15.500 1.4433 0.09469 0.08978 -0.0676 0.0040 1.0000
15.750 1.4375 0.09918 0.09439 -0.0686 0.0040 1.0000
16.000 1.4314 0.10373 0.09906 -0.0697 0.0039 1.0000
16.250 1.4248 0.10842 0.10386 -0.0709 0.0039 1.0000
16.500 1.4172 0.11328 0.10883 -0.0722 0.0038 1.0000
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