cr001sm (cr001sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.86 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr001sm-il-1000000.txt Download as CSV file: xf-cr001sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3015 0.13330 0.13166 -0.0278 1.0000 0.0067
-12.250 -0.2993 0.13036 0.12873 -0.0283 1.0000 0.0068
-12.000 -0.2970 0.12740 0.12578 -0.0286 1.0000 0.0068
-6.500 -0.1774 0.04206 0.04057 -0.0722 0.9763 0.0105
-6.250 -0.1526 0.03659 0.03507 -0.0808 0.9744 0.0106
-6.000 -0.1232 0.03131 0.02974 -0.0896 0.9730 0.0109
-5.750 -0.0987 0.02678 0.02514 -0.0960 0.9673 0.0113
-5.500 -0.0686 0.02141 0.01964 -0.1037 0.9630 0.0118
-5.250 -0.0320 0.01655 0.01457 -0.1099 0.9600 0.0143
-4.250 0.0671 0.01685 0.01323 -0.1223 0.9481 0.0149
-4.000 0.0950 0.01381 0.00989 -0.1230 0.9423 0.0135
-3.750 0.1219 0.01100 0.00663 -0.1227 0.9349 0.0124
-3.500 0.1505 0.00973 0.00515 -0.1226 0.9282 0.0128
-3.250 0.1789 0.00912 0.00442 -0.1226 0.9205 0.0138
-3.000 0.2073 0.00896 0.00419 -0.1225 0.9123 0.0145
-2.500 0.2608 0.00742 0.00245 -0.1219 0.8938 0.0172
-2.250 0.2882 0.00726 0.00226 -0.1217 0.8840 0.0195
-2.000 0.3155 0.00706 0.00198 -0.1214 0.8738 0.0208
-1.750 0.3423 0.00682 0.00165 -0.1210 0.8627 0.0219
-1.500 0.3687 0.00655 0.00130 -0.1206 0.8510 0.0257
-1.250 0.3953 0.00645 0.00115 -0.1201 0.8390 0.0289
-1.000 0.4218 0.00635 0.00098 -0.1197 0.8261 0.0362
-0.750 0.4469 0.00590 0.00088 -0.1192 0.8122 0.1762
-0.500 0.4716 0.00559 0.00088 -0.1186 0.7965 0.3148
-0.250 0.4964 0.00543 0.00089 -0.1180 0.7789 0.4146
0.000 0.5208 0.00526 0.00092 -0.1173 0.7605 0.5216
0.250 0.5429 0.00491 0.00100 -0.1160 0.7418 0.7078
0.500 0.5799 0.00442 0.00102 -0.1179 0.7226 1.0000
0.750 0.6052 0.00453 0.00104 -0.1173 0.7036 1.0000
1.000 0.6304 0.00466 0.00106 -0.1166 0.6833 1.0000
1.250 0.6555 0.00481 0.00109 -0.1159 0.6635 1.0000
1.500 0.6809 0.00494 0.00113 -0.1153 0.6432 1.0000
2.000 0.7314 0.00525 0.00125 -0.1141 0.6023 1.0000
2.250 0.7565 0.00542 0.00132 -0.1134 0.5815 1.0000
2.500 0.7818 0.00559 0.00140 -0.1129 0.5603 1.0000
2.750 0.8068 0.00577 0.00151 -0.1122 0.5388 1.0000
3.000 0.8321 0.00595 0.00160 -0.1117 0.5172 1.0000
3.250 0.8569 0.00617 0.00172 -0.1110 0.4947 1.0000
3.500 0.8819 0.00638 0.00184 -0.1104 0.4702 1.0000
3.750 0.9065 0.00661 0.00198 -0.1098 0.4444 1.0000
4.000 0.9310 0.00687 0.00213 -0.1091 0.4175 1.0000
4.250 0.9551 0.00716 0.00230 -0.1084 0.3866 1.0000
4.500 0.9787 0.00750 0.00249 -0.1076 0.3539 1.0000
4.750 1.0022 0.00785 0.00271 -0.1069 0.3190 1.0000
5.000 1.0249 0.00828 0.00297 -0.1060 0.2817 1.0000
5.250 1.0480 0.00868 0.00322 -0.1051 0.2491 1.0000
5.500 1.0708 0.00910 0.00350 -0.1043 0.2175 1.0000
5.750 1.0931 0.00957 0.00380 -0.1033 0.1857 1.0000
6.000 1.1162 0.00996 0.00410 -0.1026 0.1618 1.0000
6.250 1.1394 0.01033 0.00440 -0.1018 0.1420 1.0000
6.500 1.1621 0.01075 0.00472 -0.1009 0.1213 1.0000
6.750 1.1846 0.01118 0.00506 -0.1000 0.1013 1.0000
7.000 1.2060 0.01170 0.00546 -0.0990 0.0796 1.0000
7.250 1.2271 0.01226 0.00592 -0.0979 0.0592 1.0000
7.500 1.2479 0.01282 0.00640 -0.0967 0.0422 1.0000
7.750 1.2680 0.01345 0.00693 -0.0955 0.0281 1.0000
8.000 1.2881 0.01408 0.00751 -0.0942 0.0194 1.0000
8.250 1.3092 0.01459 0.00806 -0.0930 0.0159 1.0000
8.500 1.3295 0.01515 0.00863 -0.0918 0.0136 1.0000
8.750 1.3485 0.01584 0.00941 -0.0903 0.0116 1.0000
9.000 1.3694 0.01629 0.00990 -0.0892 0.0108 1.0000
9.250 1.3894 0.01680 0.01046 -0.0879 0.0098 1.0000
9.500 1.4066 0.01755 0.01125 -0.0862 0.0087 1.0000
9.750 1.4205 0.01855 0.01238 -0.0839 0.0078 1.0000
10.000 1.4387 0.01911 0.01300 -0.0824 0.0074 1.0000
10.250 1.4549 0.01978 0.01374 -0.0806 0.0068 1.0000
10.500 1.4693 0.02044 0.01447 -0.0785 0.0064 1.0000
10.750 1.4808 0.02121 0.01532 -0.0759 0.0060 1.0000
11.000 1.4884 0.02222 0.01640 -0.0727 0.0055 1.0000
11.250 1.4849 0.02397 0.01833 -0.0680 0.0052 1.0000
11.500 1.4854 0.02552 0.02002 -0.0642 0.0050 1.0000
11.750 1.4978 0.02625 0.02083 -0.0622 0.0049 1.0000
12.000 1.5035 0.02750 0.02219 -0.0595 0.0048 1.0000
12.250 1.5068 0.02897 0.02378 -0.0567 0.0047 1.0000
12.500 1.5106 0.03046 0.02539 -0.0542 0.0045 1.0000
12.750 1.5133 0.03212 0.02716 -0.0518 0.0043 1.0000
13.000 1.5139 0.03403 0.02921 -0.0496 0.0042 1.0000
13.250 1.5161 0.03588 0.03118 -0.0477 0.0041 1.0000
13.500 1.5168 0.03797 0.03339 -0.0461 0.0040 1.0000
13.750 1.5139 0.04054 0.03610 -0.0445 0.0039 1.0000
14.000 1.5134 0.04301 0.03867 -0.0435 0.0038 1.0000
14.250 1.5102 0.04591 0.04170 -0.0427 0.0037 1.0000
14.500 1.5036 0.04940 0.04534 -0.0422 0.0037 1.0000
14.750 1.4987 0.05290 0.04896 -0.0422 0.0036 1.0000
15.000 1.4883 0.05735 0.05357 -0.0427 0.0036 1.0000
15.250 1.4803 0.06176 0.05811 -0.0436 0.0036 1.0000
15.500 1.4669 0.06730 0.06381 -0.0452 0.0035 1.0000
15.750 1.4563 0.07269 0.06934 -0.0472 0.0035 1.0000
16.000 1.4412 0.07918 0.07599 -0.0499 0.0035 1.0000
16.250 1.4255 0.08612 0.08309 -0.0531 0.0035 1.0000
16.500 1.4106 0.09324 0.09035 -0.0567 0.0035 1.0000
16.750 1.3909 0.10166 0.09895 -0.0610 0.0035 1.0000
17.000 1.3722 0.11023 0.10767 -0.0658 0.0035 1.0000
17.250 1.3547 0.11885 0.11644 -0.0706 0.0035 1.0000
17.500 1.3338 0.12857 0.12632 -0.0763 0.0036 1.0000
17.750 1.3140 0.13837 0.13626 -0.0821 0.0036 1.0000
18.000 1.2914 0.14917 0.14722 -0.0887 0.0036 1.0000
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Polar data table (+)
Polar graphs
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