cr001sm (cr001sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 500,000 Max Cl/Cd: 120.16 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr001sm-il-500000.txt Download as CSV file: xf-cr001sm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: cr001sm
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3608 0.09535 0.09318 -0.0269 1.0000 0.0145
-7.750 -0.3675 0.09347 0.09135 -0.0252 1.0000 0.0145
-7.500 -0.3782 0.09194 0.08986 -0.0227 1.0000 0.0145
-7.250 -0.3794 0.08950 0.08746 -0.0231 0.9989 0.0145
-7.000 -0.3535 0.08417 0.08212 -0.0313 0.9956 0.0146
-6.750 -0.3281 0.07879 0.07671 -0.0394 0.9917 0.0146
-6.500 -0.3101 0.07113 0.06905 -0.0480 0.9879 0.0151
-6.250 -0.2822 0.06649 0.06439 -0.0551 0.9856 0.0154
-6.000 -0.2583 0.06261 0.06049 -0.0603 0.9811 0.0159
-5.750 -0.2276 0.05804 0.05587 -0.0678 0.9773 0.0165
-5.500 -0.1897 0.05255 0.05030 -0.0774 0.9747 0.0174
-5.250 -0.1449 0.04601 0.04362 -0.0885 0.9729 0.0192
-5.000 -0.1025 0.04041 0.03773 -0.0954 0.9667 0.0211
-4.750 -0.0636 0.03532 0.03227 -0.1012 0.9635 0.0213
-4.500 -0.0322 0.02815 0.02484 -0.1074 0.9613 0.0231
-4.250 0.0036 0.02627 0.02283 -0.1107 0.9600 0.0252
-4.000 0.0373 0.02452 0.02079 -0.1119 0.9558 0.0293
-3.750 0.0712 0.02087 0.01656 -0.1140 0.9516 0.0315
-3.500 0.1055 0.01843 0.01401 -0.1163 0.9491 0.0336
-3.250 0.1449 0.01502 0.00987 -0.1171 0.9469 0.0216
-3.000 0.1765 0.01349 0.00810 -0.1176 0.9425 0.0214
-2.750 0.2055 0.01145 0.00583 -0.1177 0.9368 0.0221
-2.500 0.2391 0.01049 0.00484 -0.1189 0.9329 0.0249
-2.250 0.2673 0.00985 0.00415 -0.1188 0.9258 0.0268
-2.000 0.2989 0.00927 0.00349 -0.1193 0.9197 0.0287
-1.750 0.3276 0.00893 0.00310 -0.1192 0.9115 0.0304
-1.500 0.3585 0.00831 0.00241 -0.1197 0.9044 0.0360
-1.250 0.3856 0.00807 0.00212 -0.1193 0.8942 0.0410
-1.000 0.4130 0.00736 0.00181 -0.1193 0.8844 0.1788
-0.750 0.4398 0.00673 0.00177 -0.1193 0.8744 0.4007
-0.500 0.4653 0.00635 0.00176 -0.1188 0.8630 0.5492
-0.250 0.4872 0.00586 0.00179 -0.1173 0.8505 0.7361
0.000 0.5288 0.00537 0.00169 -0.1199 0.8388 1.0000
0.250 0.5555 0.00543 0.00163 -0.1195 0.8238 1.0000
0.500 0.5817 0.00551 0.00159 -0.1189 0.8074 1.0000
0.750 0.6075 0.00560 0.00156 -0.1182 0.7900 1.0000
1.000 0.6331 0.00569 0.00156 -0.1176 0.7718 1.0000
1.250 0.6586 0.00581 0.00156 -0.1169 0.7534 1.0000
1.500 0.6839 0.00594 0.00159 -0.1162 0.7349 1.0000
1.750 0.7090 0.00607 0.00163 -0.1155 0.7151 1.0000
2.000 0.7340 0.00622 0.00168 -0.1147 0.6953 1.0000
2.250 0.7589 0.00638 0.00175 -0.1140 0.6750 1.0000
2.500 0.7836 0.00655 0.00183 -0.1132 0.6541 1.0000
2.750 0.8082 0.00674 0.00193 -0.1124 0.6328 1.0000
3.000 0.8327 0.00693 0.00204 -0.1116 0.6111 1.0000
3.250 0.8571 0.00714 0.00216 -0.1109 0.5884 1.0000
3.750 0.9055 0.00758 0.00246 -0.1093 0.5422 1.0000
4.000 0.9293 0.00783 0.00262 -0.1084 0.5172 1.0000
4.250 0.9529 0.00811 0.00280 -0.1075 0.4909 1.0000
4.500 0.9763 0.00840 0.00300 -0.1067 0.4624 1.0000
4.750 0.9994 0.00873 0.00321 -0.1057 0.4310 1.0000
5.000 1.0220 0.00910 0.00347 -0.1047 0.3976 1.0000
5.250 1.0442 0.00952 0.00375 -0.1037 0.3600 1.0000
5.500 1.0658 0.01001 0.00406 -0.1026 0.3194 1.0000
5.750 1.0872 0.01053 0.00440 -0.1015 0.2807 1.0000
6.000 1.1085 0.01107 0.00478 -0.1005 0.2447 1.0000
6.250 1.1297 0.01162 0.00519 -0.0994 0.2116 1.0000
6.500 1.1511 0.01215 0.00560 -0.0983 0.1820 1.0000
6.750 1.1725 0.01268 0.00601 -0.0973 0.1562 1.0000
7.000 1.1936 0.01324 0.00646 -0.0963 0.1318 1.0000
7.250 1.2144 0.01381 0.00695 -0.0951 0.1074 1.0000
7.500 1.2342 0.01447 0.00750 -0.0939 0.0822 1.0000
7.750 1.2522 0.01530 0.00817 -0.0923 0.0563 1.0000
8.000 1.2690 0.01624 0.00898 -0.0906 0.0359 1.0000
8.250 1.2856 0.01719 0.00991 -0.0887 0.0262 1.0000
8.500 1.3039 0.01794 0.01075 -0.0870 0.0224 1.0000
8.750 1.3205 0.01880 0.01167 -0.0852 0.0191 1.0000
9.000 1.3332 0.01996 0.01294 -0.0827 0.0170 1.0000
9.250 1.3497 0.02073 0.01381 -0.0809 0.0158 1.0000
9.500 1.3642 0.02159 0.01475 -0.0788 0.0145 1.0000
9.750 1.3758 0.02250 0.01573 -0.0763 0.0132 1.0000
10.000 1.3736 0.02444 0.01780 -0.0716 0.0120 1.0000
10.250 1.3845 0.02538 0.01886 -0.0691 0.0114 1.0000
10.500 1.3947 0.02639 0.01998 -0.0666 0.0108 1.0000
10.750 1.4017 0.02771 0.02142 -0.0637 0.0103 1.0000
11.000 1.4093 0.02896 0.02280 -0.0612 0.0097 1.0000
11.250 1.4152 0.03040 0.02435 -0.0586 0.0093 1.0000
11.500 1.4198 0.03199 0.02605 -0.0561 0.0090 1.0000
11.750 1.4215 0.03392 0.02808 -0.0536 0.0086 1.0000
12.000 1.4204 0.03639 0.03071 -0.0510 0.0083 1.0000
12.250 1.4160 0.03958 0.03410 -0.0484 0.0081 1.0000
12.500 1.4061 0.04396 0.03875 -0.0459 0.0079 1.0000
12.750 1.4055 0.04627 0.04125 -0.0444 0.0078 1.0000
13.000 1.4018 0.04921 0.04440 -0.0430 0.0077 1.0000
13.250 1.3954 0.05266 0.04805 -0.0420 0.0077 1.0000
13.500 1.3870 0.05652 0.05211 -0.0415 0.0076 1.0000
13.750 1.3770 0.06073 0.05654 -0.0415 0.0075 1.0000
14.000 1.3633 0.06581 0.06183 -0.0421 0.0076 1.0000
14.250 1.3488 0.07124 0.06746 -0.0434 0.0076 1.0000
14.500 1.3334 0.07720 0.07363 -0.0455 0.0076 1.0000
14.750 1.3158 0.08394 0.08057 -0.0484 0.0076 1.0000
15.000 1.2980 0.09122 0.08804 -0.0520 0.0076 1.0000
15.250 1.2792 0.09920 0.09619 -0.0564 0.0076 1.0000
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Polar data table (+)
Polar graphs
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