cr001sm (cr001sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: cr001sm (cr001sm-il) Reynolds number: 200,000 Max Cl/Cd: 83.25 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr001sm-il-200000-n5.txt Download as CSV file: xf-cr001sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3622 0.09516 0.09177 -0.0294 1.0000 0.0212
-7.500 -0.3707 0.09334 0.09002 -0.0276 1.0000 0.0212
-7.250 -0.3768 0.09126 0.08800 -0.0264 1.0000 0.0212
-7.000 -0.3660 0.08737 0.08414 -0.0301 0.9979 0.0212
-6.750 -0.3427 0.08218 0.07892 -0.0375 0.9934 0.0213
-6.500 -0.3182 0.07692 0.07363 -0.0450 0.9885 0.0213
-6.250 -0.2905 0.07143 0.06809 -0.0531 0.9845 0.0213
-6.000 -0.2738 0.06480 0.06146 -0.0593 0.9784 0.0218
-5.750 -0.2475 0.05995 0.05656 -0.0653 0.9744 0.0223
-5.500 -0.2258 0.05776 0.05436 -0.0673 0.9705 0.0243
-5.250 -0.1725 0.05149 0.04775 -0.0811 0.9640 0.0303
-5.000 -0.1455 0.04306 0.03917 -0.0871 0.9604 0.0203
-4.750 -0.1163 0.03822 0.03411 -0.0916 0.9547 0.0190
-4.500 -0.0809 0.03259 0.02807 -0.0965 0.9499 0.0178
-4.250 -0.0425 0.02719 0.02208 -0.1006 0.9470 0.0169
-4.000 -0.0090 0.02338 0.01768 -0.1027 0.9427 0.0167
-3.750 0.0222 0.02080 0.01461 -0.1036 0.9374 0.0170
-3.500 0.0573 0.01874 0.01211 -0.1052 0.9342 0.0178
-3.250 0.0942 0.01743 0.01045 -0.1069 0.9317 0.0200
-3.000 0.1219 0.01666 0.00940 -0.1066 0.9242 0.0213
-2.750 0.1551 0.01492 0.00746 -0.1077 0.9202 0.0224
-2.500 0.1865 0.01399 0.00648 -0.1083 0.9148 0.0239
-2.250 0.2171 0.01336 0.00579 -0.1088 0.9081 0.0265
-2.000 0.2519 0.01283 0.00518 -0.1100 0.9035 0.0299
-1.750 0.2798 0.01219 0.00448 -0.1100 0.8947 0.0325
-1.500 0.3133 0.01173 0.00396 -0.1110 0.8886 0.0373
-1.250 0.3430 0.01138 0.00358 -0.1112 0.8796 0.0480
-1.000 0.3735 0.01085 0.00325 -0.1117 0.8710 0.1114
-0.750 0.4041 0.01014 0.00311 -0.1126 0.8626 0.3041
-0.500 0.4278 0.00927 0.00319 -0.1118 0.8517 0.5913
-0.250 0.4669 0.00837 0.00303 -0.1135 0.8428 1.0000
0.000 0.4969 0.00838 0.00288 -0.1137 0.8312 1.0000
0.250 0.5263 0.00842 0.00277 -0.1138 0.8189 1.0000
0.500 0.5550 0.00846 0.00269 -0.1137 0.8055 1.0000
0.750 0.5829 0.00853 0.00264 -0.1135 0.7908 1.0000
1.000 0.6102 0.00861 0.00261 -0.1132 0.7747 1.0000
1.250 0.6372 0.00870 0.00259 -0.1128 0.7568 1.0000
1.500 0.6641 0.00882 0.00257 -0.1123 0.7369 1.0000
1.750 0.6901 0.00895 0.00261 -0.1117 0.7157 1.0000
2.000 0.7159 0.00911 0.00264 -0.1111 0.6943 1.0000
2.250 0.7412 0.00928 0.00270 -0.1104 0.6727 1.0000
2.500 0.7664 0.00948 0.00278 -0.1097 0.6510 1.0000
2.750 0.7912 0.00968 0.00292 -0.1089 0.6289 1.0000
3.000 0.8158 0.00991 0.00304 -0.1081 0.6067 1.0000
3.250 0.8401 0.01014 0.00319 -0.1073 0.5840 1.0000
3.500 0.8643 0.01039 0.00336 -0.1065 0.5613 1.0000
4.000 0.9116 0.01095 0.00379 -0.1047 0.5131 1.0000
4.250 0.9349 0.01127 0.00402 -0.1037 0.4872 1.0000
4.500 0.9577 0.01160 0.00428 -0.1027 0.4604 1.0000
4.750 0.9802 0.01197 0.00456 -0.1017 0.4318 1.0000
5.000 1.0021 0.01238 0.00490 -0.1005 0.4003 1.0000
5.250 1.0234 0.01284 0.00524 -0.0993 0.3667 1.0000
5.500 1.0444 0.01334 0.00562 -0.0981 0.3314 1.0000
5.750 1.0648 0.01390 0.00604 -0.0969 0.2965 1.0000
6.000 1.0853 0.01447 0.00650 -0.0957 0.2634 1.0000
6.250 1.1057 0.01507 0.00702 -0.0945 0.2336 1.0000
6.500 1.1259 0.01569 0.00755 -0.0933 0.2057 1.0000
6.750 1.1459 0.01632 0.00810 -0.0921 0.1796 1.0000
7.000 1.1656 0.01699 0.00869 -0.0908 0.1536 1.0000
7.250 1.1848 0.01771 0.00931 -0.0895 0.1269 1.0000
7.500 1.2033 0.01848 0.01001 -0.0882 0.1012 1.0000
7.750 1.2210 0.01933 0.01075 -0.0867 0.0777 1.0000
8.000 1.2380 0.02024 0.01158 -0.0851 0.0581 1.0000
8.250 1.2543 0.02120 0.01249 -0.0834 0.0433 1.0000
8.500 1.2697 0.02221 0.01350 -0.0816 0.0340 1.0000
8.750 1.2856 0.02314 0.01454 -0.0797 0.0285 1.0000
9.000 1.2981 0.02432 0.01580 -0.0775 0.0244 1.0000
9.250 1.3122 0.02524 0.01687 -0.0754 0.0214 1.0000
9.500 1.3228 0.02634 0.01806 -0.0729 0.0191 1.0000
9.750 1.3272 0.02786 0.01969 -0.0695 0.0175 1.0000
10.000 1.3358 0.02908 0.02106 -0.0669 0.0166 1.0000
10.250 1.3441 0.03034 0.02248 -0.0643 0.0154 1.0000
10.500 1.3522 0.03162 0.02389 -0.0619 0.0142 1.0000
10.750 1.3590 0.03301 0.02539 -0.0596 0.0132 1.0000
11.000 1.3616 0.03481 0.02730 -0.0570 0.0124 1.0000
11.250 1.3592 0.03725 0.02987 -0.0542 0.0119 1.0000
11.500 1.3634 0.03916 0.03199 -0.0521 0.0115 1.0000
11.750 1.3662 0.04132 0.03436 -0.0501 0.0111 1.0000
12.000 1.3679 0.04370 0.03693 -0.0483 0.0107 1.0000
12.250 1.3682 0.04629 0.03973 -0.0467 0.0104 1.0000
12.500 1.3676 0.04904 0.04269 -0.0454 0.0100 1.0000
12.750 1.3660 0.05191 0.04574 -0.0444 0.0096 1.0000
13.000 1.3632 0.05497 0.04900 -0.0437 0.0093 1.0000
13.250 1.3592 0.05829 0.05249 -0.0434 0.0090 1.0000
13.500 1.3541 0.06189 0.05626 -0.0436 0.0088 1.0000
13.750 1.3480 0.06574 0.06025 -0.0442 0.0085 1.0000
14.000 1.3390 0.07034 0.06503 -0.0451 0.0083 1.0000
14.250 1.3287 0.07535 0.07021 -0.0465 0.0082 1.0000
14.500 1.3165 0.08096 0.07601 -0.0485 0.0081 1.0000
14.750 1.3022 0.08728 0.08252 -0.0512 0.0080 1.0000
15.250 1.2734 0.10106 0.09670 -0.0580 0.0079 1.0000
15.500 1.2582 0.10872 0.10455 -0.0624 0.0079 1.0000
15.750 1.2432 0.11670 0.11272 -0.0671 0.0079 1.0000
16.000 1.2275 0.12525 0.12144 -0.0723 0.0079 1.0000
16.500 1.1969 0.14364 0.14018 -0.0839 0.0080 1.0000
16.750 1.0910 0.18878 0.18565 -0.1098 0.0105 1.0000
17.000 1.0824 0.19942 0.19623 -0.1151 0.0104 1.0000
|
Polar data table (+)
Polar graphs
<< Back to cr001sm (cr001sm-il)