CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkw-il-1000000-n5.txt Download as CSV file: xf-clarkw-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK W 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9347 0.05878 0.05633 -0.0701 1.0000 0.0180
-14.500 -1.0485 0.03472 0.03179 -0.0919 1.0000 0.0176
-14.250 -1.0624 0.03272 0.02968 -0.0883 1.0000 0.0177
-14.000 -1.0569 0.03094 0.02777 -0.0874 0.9990 0.0179
-13.750 -1.0371 0.02921 0.02589 -0.0887 0.9967 0.0182
-13.500 -1.0145 0.02779 0.02433 -0.0899 0.9949 0.0184
-13.250 -0.9909 0.02658 0.02299 -0.0908 0.9932 0.0186
-13.000 -0.9679 0.02553 0.02183 -0.0913 0.9905 0.0188
-12.750 -0.9431 0.02454 0.02071 -0.0921 0.9883 0.0190
-12.500 -0.9183 0.02340 0.01944 -0.0929 0.9864 0.0191
-12.250 -0.8941 0.02211 0.01805 -0.0937 0.9844 0.0195
-12.000 -0.8695 0.02136 0.01724 -0.0939 0.9814 0.0197
-11.750 -0.8446 0.02071 0.01653 -0.0940 0.9778 0.0199
-11.500 -0.8184 0.02004 0.01579 -0.0944 0.9748 0.0201
-11.250 -0.7909 0.01941 0.01510 -0.0949 0.9724 0.0203
-11.000 -0.7673 0.01891 0.01453 -0.0945 0.9674 0.0206
-10.750 -0.7418 0.01836 0.01392 -0.0944 0.9630 0.0208
-10.500 -0.7159 0.01776 0.01323 -0.0945 0.9594 0.0211
-10.250 -0.6926 0.01716 0.01256 -0.0939 0.9538 0.0213
-10.000 -0.6681 0.01658 0.01188 -0.0936 0.9485 0.0215
-9.750 -0.6431 0.01602 0.01124 -0.0933 0.9436 0.0217
-9.500 -0.6186 0.01555 0.01069 -0.0928 0.9375 0.0220
-9.250 -0.5933 0.01510 0.01016 -0.0925 0.9316 0.0223
-9.000 -0.5681 0.01464 0.00962 -0.0921 0.9259 0.0225
-8.750 -0.5429 0.01419 0.00909 -0.0917 0.9192 0.0226
-8.500 -0.5172 0.01378 0.00860 -0.0913 0.9133 0.0228
-8.250 -0.4915 0.01339 0.00814 -0.0910 0.9065 0.0229
-8.000 -0.4656 0.01304 0.00771 -0.0906 0.8997 0.0230
-7.750 -0.4402 0.01255 0.00714 -0.0902 0.8931 0.0232
-7.500 -0.4153 0.01199 0.00651 -0.0898 0.8857 0.0236
-7.250 -0.3894 0.01159 0.00605 -0.0894 0.8792 0.0239
-7.000 -0.3630 0.01127 0.00569 -0.0891 0.8719 0.0243
-6.750 -0.3365 0.01099 0.00535 -0.0889 0.8652 0.0246
-6.500 -0.3097 0.01071 0.00503 -0.0886 0.8581 0.0249
-6.250 -0.2830 0.01046 0.00471 -0.0883 0.8510 0.0251
-6.000 -0.2560 0.01021 0.00442 -0.0881 0.8443 0.0254
-5.750 -0.2290 0.00999 0.00414 -0.0879 0.8371 0.0257
-5.500 -0.2019 0.00977 0.00388 -0.0877 0.8304 0.0260
-5.250 -0.1750 0.00957 0.00362 -0.0874 0.8214 0.0263
-5.000 -0.1481 0.00940 0.00339 -0.0871 0.8103 0.0266
-4.750 -0.1214 0.00925 0.00316 -0.0867 0.7980 0.0269
-4.500 -0.0945 0.00910 0.00296 -0.0864 0.7870 0.0272
-4.250 -0.0671 0.00896 0.00277 -0.0862 0.7783 0.0275
-4.000 -0.0400 0.00884 0.00260 -0.0860 0.7690 0.0277
-3.750 -0.0126 0.00868 0.00240 -0.0858 0.7596 0.0282
-3.500 0.0144 0.00853 0.00221 -0.0855 0.7503 0.0291
-3.250 0.0417 0.00841 0.00206 -0.0853 0.7404 0.0300
-3.000 0.0690 0.00831 0.00193 -0.0851 0.7309 0.0308
-2.750 0.0962 0.00824 0.00181 -0.0848 0.7207 0.0315
-2.500 0.1236 0.00816 0.00170 -0.0846 0.7100 0.0324
-2.250 0.1509 0.00811 0.00161 -0.0844 0.6991 0.0333
-2.000 0.1779 0.00805 0.00152 -0.0841 0.6875 0.0361
-1.750 0.2049 0.00796 0.00143 -0.0838 0.6755 0.0434
-1.500 0.2312 0.00778 0.00135 -0.0835 0.6629 0.0776
-1.250 0.2579 0.00772 0.00131 -0.0832 0.6495 0.0938
-1.000 0.2846 0.00769 0.00128 -0.0829 0.6355 0.1076
-0.750 0.3111 0.00765 0.00125 -0.0825 0.6204 0.1252
-0.500 0.3375 0.00763 0.00123 -0.0822 0.6047 0.1470
-0.250 0.3636 0.00759 0.00123 -0.0818 0.5878 0.1768
0.000 0.3896 0.00757 0.00125 -0.0814 0.5697 0.2081
0.250 0.4157 0.00759 0.00127 -0.0810 0.5504 0.2343
0.500 0.4418 0.00765 0.00131 -0.0806 0.5300 0.2548
0.750 0.4678 0.00773 0.00136 -0.0802 0.5104 0.2733
1.000 0.4939 0.00779 0.00142 -0.0799 0.4916 0.2967
1.250 0.5200 0.00788 0.00150 -0.0795 0.4720 0.3190
1.500 0.5462 0.00798 0.00157 -0.0791 0.4543 0.3341
1.750 0.5726 0.00806 0.00164 -0.0788 0.4399 0.3514
2.000 0.5989 0.00813 0.00172 -0.0785 0.4270 0.3764
2.250 0.6252 0.00819 0.00180 -0.0782 0.4144 0.3991
2.500 0.6516 0.00825 0.00188 -0.0779 0.4024 0.4216
2.750 0.6775 0.00827 0.00197 -0.0776 0.3907 0.4639
3.000 0.6918 0.00735 0.00213 -0.0749 0.3794 0.8680
3.250 0.7159 0.00739 0.00229 -0.0738 0.3669 0.9389
3.500 0.7470 0.00754 0.00242 -0.0744 0.3552 0.9630
3.750 0.7794 0.00771 0.00255 -0.0755 0.3447 0.9757
4.000 0.8120 0.00790 0.00268 -0.0766 0.3332 0.9849
4.250 0.8446 0.00808 0.00281 -0.0777 0.3215 0.9904
4.500 0.8769 0.00826 0.00295 -0.0788 0.3107 0.9946
4.750 0.9100 0.00850 0.00311 -0.0801 0.2956 0.9976
5.000 0.9409 0.00875 0.00328 -0.0809 0.2790 1.0000
5.250 0.9622 0.00898 0.00344 -0.0796 0.2638 1.0000
5.500 0.9832 0.00923 0.00362 -0.0783 0.2468 1.0000
5.750 1.0047 0.00947 0.00379 -0.0771 0.2332 1.0000
6.000 1.0263 0.00973 0.00398 -0.0759 0.2197 1.0000
6.250 1.0476 0.01002 0.00420 -0.0747 0.2033 1.0000
6.500 1.0688 0.01035 0.00445 -0.0735 0.1848 1.0000
6.750 1.0889 0.01078 0.00475 -0.0721 0.1614 1.0000
7.000 1.1081 0.01129 0.00511 -0.0706 0.1355 1.0000
7.250 1.1287 0.01172 0.00545 -0.0694 0.1182 1.0000
7.500 1.1497 0.01212 0.00578 -0.0683 0.1053 1.0000
7.750 1.1707 0.01252 0.00612 -0.0672 0.0935 1.0000
8.000 1.1911 0.01296 0.00649 -0.0660 0.0800 1.0000
8.250 1.2108 0.01344 0.00689 -0.0647 0.0656 1.0000
8.500 1.2303 0.01392 0.00730 -0.0634 0.0549 1.0000
8.750 1.2503 0.01436 0.00771 -0.0622 0.0480 1.0000
9.000 1.2695 0.01480 0.00812 -0.0608 0.0428 1.0000
9.250 1.2885 0.01518 0.00850 -0.0594 0.0395 1.0000
9.500 1.3065 0.01562 0.00894 -0.0578 0.0364 1.0000
9.750 1.3254 0.01601 0.00934 -0.0564 0.0346 1.0000
10.000 1.3434 0.01646 0.00980 -0.0550 0.0325 1.0000
10.250 1.3606 0.01696 0.01030 -0.0534 0.0304 1.0000
10.500 1.3787 0.01740 0.01077 -0.0520 0.0293 1.0000
10.750 1.3961 0.01788 0.01128 -0.0506 0.0279 1.0000
11.000 1.4123 0.01844 0.01186 -0.0491 0.0263 1.0000
11.250 1.4281 0.01904 0.01247 -0.0475 0.0249 1.0000
11.500 1.4446 0.01959 0.01306 -0.0461 0.0238 1.0000
11.750 1.4600 0.02021 0.01371 -0.0446 0.0225 1.0000
12.000 1.4742 0.02093 0.01445 -0.0430 0.0212 1.0000
12.250 1.4885 0.02165 0.01521 -0.0415 0.0201 1.0000
12.500 1.5024 0.02241 0.01600 -0.0400 0.0189 1.0000
12.750 1.5149 0.02328 0.01690 -0.0385 0.0176 1.0000
13.000 1.5268 0.02421 0.01786 -0.0370 0.0166 1.0000
13.250 1.5388 0.02516 0.01886 -0.0355 0.0157 1.0000
13.500 1.5498 0.02622 0.01996 -0.0341 0.0149 1.0000
13.750 1.5594 0.02740 0.02118 -0.0326 0.0142 1.0000
14.000 1.5682 0.02867 0.02251 -0.0312 0.0135 1.0000
14.250 1.5776 0.02995 0.02385 -0.0299 0.0131 1.0000
14.500 1.5858 0.03135 0.02531 -0.0287 0.0126 1.0000
14.750 1.5928 0.03289 0.02691 -0.0275 0.0121 1.0000
15.000 1.5985 0.03459 0.02867 -0.0264 0.0116 1.0000
15.250 1.6028 0.03648 0.03062 -0.0253 0.0111 1.0000
15.500 1.6061 0.03851 0.03272 -0.0243 0.0107 1.0000
15.750 1.6105 0.04051 0.03480 -0.0235 0.0105 1.0000
16.000 1.6138 0.04270 0.03707 -0.0229 0.0102 1.0000
16.250 1.6159 0.04509 0.03954 -0.0224 0.0100 1.0000
16.500 1.6166 0.04770 0.04224 -0.0220 0.0097 1.0000
16.750 1.6162 0.05054 0.04516 -0.0218 0.0095 1.0000
17.000 1.6147 0.05361 0.04831 -0.0217 0.0093 1.0000
17.250 1.6116 0.05695 0.05174 -0.0219 0.0091 1.0000
17.500 1.6069 0.06058 0.05546 -0.0222 0.0089 1.0000
17.750 1.6009 0.06448 0.05946 -0.0227 0.0087 1.0000
18.000 1.5930 0.06877 0.06385 -0.0235 0.0085 1.0000
18.250 1.5842 0.07326 0.06844 -0.0245 0.0084 1.0000
18.500 1.5761 0.07773 0.07302 -0.0256 0.0083 1.0000
18.750 1.5668 0.08245 0.07785 -0.0268 0.0082 1.0000
19.000 1.5569 0.08734 0.08285 -0.0282 0.0081 1.0000
19.250 1.5452 0.09255 0.08817 -0.0299 0.0081 1.0000
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