WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: WACO COOTIE AIRFOIL (cootie-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.11 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cootie-il-1000000-n5.txt Download as CSV file: xf-cootie-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3081 0.09922 0.09730 -0.0360 0.8839 0.0063
-9.750 -0.3069 0.09476 0.09280 -0.0381 0.8751 0.0067
-9.500 -0.3134 0.08833 0.08635 -0.0415 0.8668 0.0073
-9.250 -0.3059 0.08554 0.08354 -0.0432 0.8602 0.0075
-9.000 -0.2976 0.08283 0.08081 -0.0451 0.8536 0.0077
-8.750 -0.2902 0.08005 0.07802 -0.0472 0.8471 0.0079
-8.500 -0.2791 0.07669 0.07464 -0.0510 0.8414 0.0082
-8.250 -0.2668 0.07233 0.07025 -0.0562 0.8354 0.0088
-8.000 -0.2554 0.06398 0.06185 -0.0668 0.8298 0.0101
-7.750 -0.2347 0.06115 0.05897 -0.0706 0.8243 0.0103
-7.500 -0.2193 0.01699 0.01305 -0.1083 0.8198 0.0172
-7.250 -0.1922 0.01613 0.01204 -0.1086 0.8153 0.0177
-7.000 -0.1641 0.01609 0.01199 -0.1087 0.8101 0.0180
-6.750 -0.1361 0.01607 0.01195 -0.1087 0.8048 0.0183
-6.500 -0.1082 0.01595 0.01179 -0.1088 0.7996 0.0186
-6.250 -0.0801 0.01580 0.01160 -0.1089 0.7935 0.0191
-6.000 -0.0525 0.01516 0.01080 -0.1091 0.7874 0.0196
-5.750 -0.0246 0.01454 0.01005 -0.1094 0.7808 0.0203
-5.500 0.0033 0.01388 0.00922 -0.1095 0.7734 0.0209
-5.250 0.0314 0.01319 0.00836 -0.1097 0.7658 0.0214
-5.000 0.0594 0.01273 0.00774 -0.1098 0.7565 0.0218
-4.750 0.0876 0.01235 0.00723 -0.1100 0.7457 0.0222
-4.500 0.1157 0.01191 0.00664 -0.1101 0.7313 0.0224
-4.250 0.1435 0.01153 0.00608 -0.1101 0.7105 0.0225
-4.000 0.1711 0.01123 0.00558 -0.1101 0.6833 0.0226
-3.750 0.1987 0.01098 0.00514 -0.1101 0.6579 0.0227
-3.500 0.2264 0.01075 0.00475 -0.1101 0.6383 0.0228
-3.250 0.2543 0.00993 0.00374 -0.1103 0.6252 0.0234
-3.000 0.2825 0.00955 0.00326 -0.1104 0.6158 0.0238
-2.750 0.3107 0.00929 0.00293 -0.1105 0.6077 0.0242
-2.500 0.3392 0.00907 0.00267 -0.1107 0.6010 0.0247
-2.250 0.3676 0.00892 0.00247 -0.1108 0.5941 0.0251
-2.000 0.3961 0.00878 0.00229 -0.1109 0.5874 0.0257
-1.750 0.4245 0.00868 0.00214 -0.1111 0.5803 0.0261
-1.500 0.4530 0.00858 0.00201 -0.1112 0.5741 0.0266
-1.250 0.4815 0.00849 0.00189 -0.1114 0.5678 0.0270
-1.000 0.5099 0.00843 0.00180 -0.1115 0.5616 0.0273
-0.750 0.5384 0.00837 0.00171 -0.1117 0.5545 0.0276
-0.500 0.5667 0.00834 0.00164 -0.1118 0.5468 0.0279
-0.250 0.5952 0.00830 0.00159 -0.1120 0.5392 0.0282
0.000 0.6234 0.00830 0.00156 -0.1121 0.5319 0.0286
0.250 0.6518 0.00829 0.00153 -0.1122 0.5242 0.0292
0.500 0.6800 0.00831 0.00152 -0.1124 0.5159 0.0295
0.750 0.7082 0.00834 0.00151 -0.1125 0.5061 0.0298
1.000 0.7362 0.00838 0.00152 -0.1126 0.4954 0.0302
1.250 0.7639 0.00846 0.00154 -0.1127 0.4802 0.0327
1.500 0.7913 0.00856 0.00159 -0.1127 0.4609 0.0391
1.750 0.8186 0.00863 0.00171 -0.1128 0.4439 0.0795
2.000 0.8461 0.00875 0.00180 -0.1129 0.4300 0.0866
2.250 0.8734 0.00887 0.00190 -0.1129 0.4157 0.0933
2.500 0.9002 0.00905 0.00202 -0.1129 0.3971 0.0989
2.750 0.9266 0.00928 0.00217 -0.1129 0.3732 0.1062
3.000 0.9533 0.00946 0.00232 -0.1128 0.3561 0.1198
3.250 0.9803 0.00955 0.00247 -0.1129 0.3438 0.1674
3.750 1.0282 0.00849 0.00295 -0.1121 0.3181 1.0000
4.000 1.0543 0.00876 0.00314 -0.1120 0.3005 1.0000
4.250 1.0806 0.00900 0.00331 -0.1119 0.2863 1.0000
4.500 1.1062 0.00931 0.00352 -0.1118 0.2670 1.0000
4.750 1.1302 0.00978 0.00380 -0.1114 0.2330 1.0000
5.000 1.1515 0.01053 0.00425 -0.1106 0.1796 1.0000
5.250 1.1698 0.01158 0.00492 -0.1094 0.1113 1.0000
5.500 1.1909 0.01230 0.00543 -0.1086 0.0759 1.0000
5.750 1.2151 0.01267 0.00576 -0.1082 0.0644 1.0000
6.000 1.2338 0.01359 0.00642 -0.1070 0.0221 1.0000
6.250 1.2566 0.01406 0.00687 -0.1063 0.0139 1.0000
6.500 1.2804 0.01440 0.00723 -0.1059 0.0117 1.0000
6.750 1.3040 0.01474 0.00761 -0.1054 0.0108 1.0000
7.000 1.3269 0.01513 0.00803 -0.1048 0.0097 1.0000
7.250 1.3486 0.01561 0.00853 -0.1041 0.0085 1.0000
7.500 1.3707 0.01602 0.00898 -0.1034 0.0079 1.0000
7.750 1.3924 0.01644 0.00942 -0.1026 0.0074 1.0000
8.000 1.4132 0.01690 0.00992 -0.1017 0.0069 1.0000
8.250 1.4333 0.01740 0.01044 -0.1007 0.0064 1.0000
8.500 1.4516 0.01799 0.01106 -0.0995 0.0059 1.0000
8.750 1.4682 0.01864 0.01177 -0.0979 0.0056 1.0000
9.000 1.4852 0.01919 0.01237 -0.0964 0.0054 1.0000
9.250 1.4995 0.01977 0.01299 -0.0944 0.0052 1.0000
9.500 1.5129 0.02040 0.01369 -0.0924 0.0049 1.0000
9.750 1.5262 0.02108 0.01441 -0.0905 0.0046 1.0000
10.000 1.5391 0.02182 0.01520 -0.0886 0.0044 1.0000
10.250 1.5508 0.02267 0.01610 -0.0867 0.0042 1.0000
10.500 1.5613 0.02365 0.01714 -0.0848 0.0041 1.0000
10.750 1.5692 0.02487 0.01842 -0.0827 0.0039 1.0000
11.000 1.5755 0.02627 0.01991 -0.0806 0.0037 1.0000
11.250 1.5844 0.02751 0.02125 -0.0789 0.0037 1.0000
11.500 1.5922 0.02890 0.02272 -0.0773 0.0036 1.0000
11.750 1.5991 0.03042 0.02432 -0.0757 0.0035 1.0000
12.000 1.6049 0.03207 0.02606 -0.0742 0.0034 1.0000
12.250 1.6096 0.03390 0.02798 -0.0727 0.0033 1.0000
12.500 1.6132 0.03588 0.03005 -0.0714 0.0033 1.0000
12.750 1.6160 0.03800 0.03226 -0.0701 0.0032 1.0000
13.000 1.6181 0.04028 0.03463 -0.0691 0.0031 1.0000
13.250 1.6192 0.04274 0.03719 -0.0681 0.0030 1.0000
13.500 1.6194 0.04537 0.03991 -0.0673 0.0030 1.0000
13.750 1.6184 0.04825 0.04290 -0.0667 0.0029 1.0000
14.000 1.6176 0.05123 0.04598 -0.0663 0.0029 1.0000
14.250 1.6164 0.05435 0.04919 -0.0661 0.0028 1.0000
14.500 1.6137 0.05775 0.05269 -0.0660 0.0028 1.0000
14.750 1.6116 0.06118 0.05621 -0.0661 0.0027 1.0000
15.000 1.6077 0.06492 0.06005 -0.0663 0.0027 1.0000
15.250 1.6022 0.06891 0.06414 -0.0667 0.0026 1.0000
15.500 1.5955 0.07318 0.06850 -0.0672 0.0026 1.0000
15.750 1.5873 0.07775 0.07318 -0.0679 0.0025 1.0000
16.000 1.5775 0.08266 0.07821 -0.0687 0.0025 1.0000
16.250 1.5652 0.08803 0.08369 -0.0698 0.0024 1.0000
16.500 1.5515 0.09372 0.08950 -0.0711 0.0024 1.0000
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