cr001sm (cr001sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.68 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr001sm-il-1000000-n5.txt Download as CSV file: xf-cr001sm-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2999 0.13314 0.13150 -0.0267 1.0000 0.0052
-12.250 -0.2970 0.13042 0.12879 -0.0270 1.0000 0.0055
-11.750 -0.4016 0.13456 0.13278 -0.0201 1.0000 0.0046
-11.500 -0.3957 0.13202 0.13025 -0.0208 1.0000 0.0050
-11.250 -0.3942 0.12745 0.12569 -0.0218 1.0000 0.0045
-9.750 -0.3695 0.10989 0.10821 -0.0254 1.0000 0.0066
-9.500 -0.3676 0.10695 0.10528 -0.0258 1.0000 0.0066
-9.250 -0.3663 0.10408 0.10242 -0.0258 1.0000 0.0066
-8.750 -0.3501 0.09760 0.09597 -0.0295 0.9990 0.0060
-8.500 -0.3364 0.09289 0.09126 -0.0346 0.9974 0.0067
-8.000 -0.3149 0.08574 0.08412 -0.0401 0.9927 0.0061
-7.750 -0.3028 0.08188 0.08026 -0.0440 0.9892 0.0059
-7.500 -0.2892 0.07759 0.07598 -0.0489 0.9856 0.0057
-7.250 -0.2779 0.07350 0.07188 -0.0533 0.9791 0.0054
-7.000 -0.2575 0.06804 0.06642 -0.0613 0.9750 0.0053
-6.750 -0.2329 0.06167 0.06003 -0.0714 0.9704 0.0051
-6.500 -0.2045 0.05483 0.05314 -0.0826 0.9635 0.0052
-6.250 -0.1598 0.04487 0.04304 -0.0999 0.9597 0.0052
-6.000 -0.1226 0.03349 0.03134 -0.1131 0.9503 0.0057
-5.750 -0.1016 0.01324 0.00929 -0.1208 0.9371 0.0064
-5.500 -0.0719 0.01198 0.00775 -0.1216 0.9308 0.0066
-5.250 -0.0440 0.01134 0.00695 -0.1217 0.9225 0.0067
-5.000 -0.0169 0.00993 0.00524 -0.1218 0.9141 0.0072
-4.750 0.0111 0.00938 0.00457 -0.1219 0.9051 0.0075
-4.500 0.0385 0.00904 0.00415 -0.1218 0.8954 0.0078
-4.250 0.0660 0.00874 0.00376 -0.1217 0.8855 0.0083
-4.000 0.0931 0.00845 0.00337 -0.1215 0.8752 0.0089
-3.750 0.1198 0.00817 0.00300 -0.1212 0.8641 0.0094
-3.500 0.1465 0.00796 0.00270 -0.1208 0.8530 0.0099
-3.250 0.1728 0.00765 0.00230 -0.1204 0.8417 0.0105
-3.000 0.1992 0.00747 0.00205 -0.1200 0.8298 0.0114
-2.750 0.2256 0.00737 0.00189 -0.1196 0.8172 0.0124
-2.500 0.2520 0.00729 0.00175 -0.1192 0.8044 0.0137
-2.250 0.2782 0.00723 0.00161 -0.1188 0.7908 0.0144
-2.000 0.3043 0.00707 0.00136 -0.1183 0.7768 0.0155
-1.750 0.3304 0.00696 0.00118 -0.1178 0.7623 0.0173
-1.500 0.3566 0.00692 0.00108 -0.1174 0.7476 0.0193
-1.250 0.3827 0.00690 0.00099 -0.1169 0.7323 0.0208
-1.000 0.4088 0.00688 0.00089 -0.1164 0.7159 0.0239
-0.750 0.4346 0.00687 0.00084 -0.1159 0.6980 0.0325
-0.500 0.4598 0.00679 0.00080 -0.1153 0.6782 0.0774
-0.250 0.4848 0.00668 0.00079 -0.1147 0.6546 0.1504
0.000 0.5097 0.00662 0.00080 -0.1142 0.6307 0.2209
0.250 0.5343 0.00650 0.00085 -0.1136 0.6077 0.3247
0.500 0.5591 0.00637 0.00092 -0.1131 0.5863 0.4324
0.750 0.5832 0.00619 0.00102 -0.1124 0.5663 0.5726
1.000 0.6072 0.00608 0.00110 -0.1116 0.5457 0.6808
1.250 0.6282 0.00585 0.00119 -0.1101 0.5266 0.8282
1.750 0.6926 0.00590 0.00132 -0.1120 0.4849 1.0000
2.000 0.7182 0.00608 0.00139 -0.1115 0.4656 1.0000
2.250 0.7439 0.00625 0.00147 -0.1110 0.4458 1.0000
2.750 0.7947 0.00664 0.00168 -0.1100 0.4030 1.0000
3.000 0.8198 0.00687 0.00179 -0.1095 0.3797 1.0000
3.250 0.8447 0.00710 0.00192 -0.1089 0.3554 1.0000
3.500 0.8693 0.00738 0.00207 -0.1083 0.3276 1.0000
3.750 0.8936 0.00768 0.00224 -0.1076 0.2988 1.0000
4.000 0.9179 0.00798 0.00244 -0.1070 0.2716 1.0000
4.250 0.9420 0.00831 0.00264 -0.1063 0.2443 1.0000
4.500 0.9663 0.00861 0.00284 -0.1057 0.2218 1.0000
4.750 0.9905 0.00892 0.00305 -0.1050 0.2006 1.0000
5.000 1.0146 0.00924 0.00329 -0.1044 0.1791 1.0000
5.250 1.0384 0.00957 0.00353 -0.1037 0.1595 1.0000
5.500 1.0623 0.00990 0.00378 -0.1030 0.1400 1.0000
5.750 1.0848 0.01035 0.00409 -0.1021 0.1132 1.0000
6.000 1.1074 0.01080 0.00441 -0.1013 0.0910 1.0000
6.250 1.1306 0.01118 0.00473 -0.1005 0.0754 1.0000
6.500 1.1535 0.01158 0.00507 -0.0996 0.0608 1.0000
6.750 1.1761 0.01200 0.00543 -0.0988 0.0483 1.0000
7.000 1.1985 0.01243 0.00582 -0.0979 0.0375 1.0000
7.250 1.2205 0.01289 0.00624 -0.0969 0.0279 1.0000
7.500 1.2427 0.01333 0.00665 -0.0960 0.0212 1.0000
7.750 1.2647 0.01377 0.00708 -0.0950 0.0163 1.0000
8.000 1.2862 0.01423 0.00753 -0.0940 0.0130 1.0000
8.250 1.3082 0.01464 0.00797 -0.0931 0.0110 1.0000
8.500 1.3297 0.01508 0.00843 -0.0921 0.0097 1.0000
8.750 1.3501 0.01560 0.00899 -0.0909 0.0081 1.0000
9.000 1.3712 0.01604 0.00947 -0.0898 0.0075 1.0000
9.250 1.3919 0.01648 0.00996 -0.0887 0.0069 1.0000
9.500 1.4117 0.01699 0.01050 -0.0875 0.0063 1.0000
9.750 1.4306 0.01755 0.01110 -0.0861 0.0056 1.0000
10.000 1.4481 0.01820 0.01181 -0.0845 0.0050 1.0000
10.250 1.4667 0.01872 0.01241 -0.0830 0.0048 1.0000
10.500 1.4843 0.01927 0.01303 -0.0815 0.0045 1.0000
10.750 1.4995 0.01987 0.01369 -0.0795 0.0042 1.0000
11.000 1.5136 0.02047 0.01435 -0.0773 0.0039 1.0000
11.250 1.5264 0.02113 0.01507 -0.0750 0.0037 1.0000
11.500 1.5381 0.02187 0.01587 -0.0725 0.0034 1.0000
11.750 1.5467 0.02282 0.01691 -0.0697 0.0031 1.0000
12.000 1.5549 0.02381 0.01799 -0.0669 0.0030 1.0000
12.250 1.5641 0.02473 0.01901 -0.0645 0.0029 1.0000
12.500 1.5734 0.02566 0.02005 -0.0621 0.0028 1.0000
12.750 1.5812 0.02672 0.02120 -0.0598 0.0027 1.0000
13.000 1.5877 0.02791 0.02249 -0.0574 0.0026 1.0000
13.250 1.5928 0.02924 0.02394 -0.0550 0.0026 1.0000
13.500 1.5973 0.03067 0.02548 -0.0528 0.0025 1.0000
13.750 1.6011 0.03224 0.02715 -0.0507 0.0024 1.0000
14.000 1.6024 0.03408 0.02911 -0.0487 0.0024 1.0000
14.250 1.6045 0.03595 0.03109 -0.0470 0.0023 1.0000
14.500 1.6045 0.03812 0.03338 -0.0455 0.0022 1.0000
14.750 1.6063 0.04022 0.03557 -0.0443 0.0021 1.0000
15.000 1.6031 0.04297 0.03845 -0.0433 0.0021 1.0000
15.250 1.6029 0.04553 0.04112 -0.0426 0.0020 1.0000
15.500 1.5962 0.04903 0.04476 -0.0423 0.0020 1.0000
15.750 1.5929 0.05230 0.04814 -0.0423 0.0020 1.0000
16.000 1.5851 0.05638 0.05235 -0.0428 0.0019 1.0000
16.250 1.5753 0.06099 0.05712 -0.0438 0.0019 1.0000
16.500 1.5662 0.06581 0.06207 -0.0451 0.0019 1.0000
16.750 1.5519 0.07172 0.06814 -0.0473 0.0019 1.0000
17.000 1.5358 0.07829 0.07485 -0.0500 0.0018 1.0000
17.250 1.5201 0.08514 0.08185 -0.0532 0.0018 1.0000
17.500 1.5017 0.09280 0.08966 -0.0569 0.0018 1.0000
17.750 1.4813 0.10120 0.09822 -0.0613 0.0018 1.0000
18.000 1.4575 0.11068 0.10787 -0.0664 0.0018 1.0000
18.250 1.4349 0.12018 0.11751 -0.0717 0.0018 1.0000
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