AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.35 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w145-il-1000000.txt Download as CSV file: xf-ah93w145-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-145
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7557 0.09317 0.09105 -0.0436 1.0000 0.0122
-15.250 -0.8017 0.08074 0.07848 -0.0509 1.0000 0.0120
-15.000 -0.8298 0.07152 0.06915 -0.0566 1.0000 0.0119
-14.750 -0.8658 0.06038 0.05786 -0.0643 1.0000 0.0118
-14.500 -0.9044 0.04811 0.04535 -0.0746 1.0000 0.0117
-14.250 -0.9199 0.04134 0.03840 -0.0807 1.0000 0.0117
-14.000 -0.9267 0.03718 0.03408 -0.0838 1.0000 0.0118
-13.750 -0.9375 0.03359 0.03033 -0.0851 1.0000 0.0118
-13.500 -0.9600 0.03039 0.02695 -0.0832 1.0000 0.0120
-13.250 -0.9766 0.02825 0.02466 -0.0794 1.0000 0.0121
-13.000 -0.9781 0.02647 0.02275 -0.0768 1.0000 0.0123
-12.750 -0.9714 0.02520 0.02139 -0.0748 1.0000 0.0125
-12.500 -0.9510 0.02404 0.02016 -0.0751 0.9988 0.0127
-12.250 -0.9172 0.02291 0.01894 -0.0778 0.9947 0.0131
-12.000 -0.8870 0.02188 0.01783 -0.0796 0.9859 0.0134
-11.750 -0.8519 0.02082 0.01666 -0.0823 0.9697 0.0138
-11.500 -0.7952 0.01963 0.01519 -0.0895 0.8999 0.0143
-11.250 -0.7754 0.01924 0.01442 -0.0884 0.8291 0.0146
-11.000 -0.7536 0.01878 0.01375 -0.0878 0.7949 0.0148
-10.750 -0.7331 0.01790 0.01264 -0.0872 0.7691 0.0151
-10.500 -0.7124 0.01692 0.01151 -0.0867 0.7472 0.0157
-10.250 -0.6884 0.01642 0.01088 -0.0865 0.7280 0.0162
-10.000 -0.6635 0.01601 0.01036 -0.0863 0.7113 0.0166
-9.750 -0.6381 0.01563 0.00988 -0.0862 0.6969 0.0172
-9.500 -0.6123 0.01527 0.00941 -0.0860 0.6846 0.0178
-9.250 -0.5860 0.01497 0.00900 -0.0860 0.6738 0.0183
-9.000 -0.5610 0.01433 0.00824 -0.0858 0.6644 0.0189
-8.750 -0.5356 0.01377 0.00761 -0.0857 0.6562 0.0198
-8.500 -0.5088 0.01344 0.00722 -0.0858 0.6484 0.0206
-8.250 -0.4819 0.01315 0.00686 -0.0858 0.6414 0.0215
-8.000 -0.4545 0.01287 0.00650 -0.0858 0.6351 0.0223
-7.750 -0.4278 0.01247 0.00602 -0.0858 0.6291 0.0233
-7.500 -0.4007 0.01211 0.00564 -0.0859 0.6241 0.0249
-7.250 -0.3728 0.01188 0.00538 -0.0860 0.6194 0.0263
-7.000 -0.3449 0.01170 0.00512 -0.0861 0.6147 0.0274
-6.750 -0.3177 0.01131 0.00469 -0.0861 0.6103 0.0296
-6.500 -0.2895 0.01109 0.00446 -0.0863 0.6066 0.0316
-6.250 -0.2611 0.01095 0.00427 -0.0865 0.6025 0.0333
-6.000 -0.2333 0.01064 0.00394 -0.0866 0.5986 0.0367
-5.750 -0.2051 0.01051 0.00377 -0.0867 0.5946 0.0393
-5.500 -0.1766 0.01028 0.00353 -0.0870 0.5919 0.0425
-5.250 -0.1481 0.01008 0.00334 -0.0872 0.5889 0.0463
-5.000 -0.1194 0.00996 0.00319 -0.0874 0.5857 0.0492
-4.750 -0.0910 0.00976 0.00299 -0.0876 0.5825 0.0552
-4.500 -0.0625 0.00969 0.00287 -0.0878 0.5788 0.0590
-4.250 -0.0337 0.00947 0.00270 -0.0880 0.5765 0.0671
-4.000 -0.0048 0.00932 0.00256 -0.0883 0.5738 0.0747
-3.750 0.0241 0.00919 0.00244 -0.0886 0.5712 0.0836
-3.500 0.0529 0.00905 0.00233 -0.0888 0.5685 0.0959
-3.250 0.0816 0.00892 0.00223 -0.0891 0.5658 0.1126
-3.000 0.1103 0.00880 0.00216 -0.0894 0.5628 0.1325
-2.750 0.1395 0.00864 0.00208 -0.0897 0.5607 0.1553
-2.500 0.1685 0.00847 0.00200 -0.0901 0.5583 0.1825
-2.250 0.1976 0.00830 0.00193 -0.0905 0.5559 0.2165
-2.000 0.2266 0.00810 0.00187 -0.0909 0.5535 0.2637
-1.750 0.2554 0.00785 0.00182 -0.0913 0.5512 0.3321
-1.500 0.2842 0.00758 0.00180 -0.0918 0.5484 0.4219
-1.250 0.3133 0.00732 0.00179 -0.0923 0.5463 0.5065
-1.000 0.3426 0.00710 0.00179 -0.0928 0.5442 0.5786
-0.750 0.3718 0.00695 0.00180 -0.0931 0.5420 0.6367
-0.500 0.4009 0.00686 0.00183 -0.0934 0.5398 0.6831
-0.250 0.4299 0.00681 0.00186 -0.0936 0.5376 0.7189
0.000 0.4586 0.00681 0.00191 -0.0938 0.5354 0.7484
0.250 0.4872 0.00685 0.00197 -0.0939 0.5327 0.7730
0.500 0.5159 0.00687 0.00204 -0.0941 0.5307 0.7944
0.750 0.5447 0.00687 0.00209 -0.0942 0.5287 0.8105
1.000 0.5735 0.00690 0.00214 -0.0944 0.5267 0.8238
1.250 0.6023 0.00693 0.00219 -0.0945 0.5246 0.8370
1.500 0.6307 0.00698 0.00224 -0.0946 0.5225 0.8493
1.750 0.6584 0.00704 0.00233 -0.0945 0.5202 0.8651
2.000 0.6854 0.00714 0.00243 -0.0942 0.5176 0.8787
2.250 0.7134 0.00720 0.00251 -0.0942 0.5155 0.8869
2.500 0.7415 0.00723 0.00258 -0.0943 0.5136 0.8946
2.750 0.7696 0.00727 0.00264 -0.0943 0.5114 0.9014
3.000 0.7972 0.00731 0.00270 -0.0943 0.5091 0.9081
3.250 0.8254 0.00736 0.00276 -0.0944 0.5068 0.9147
3.500 0.8520 0.00742 0.00283 -0.0941 0.5044 0.9209
3.750 0.8795 0.00754 0.00293 -0.0941 0.5015 0.9276
4.000 0.9060 0.00755 0.00300 -0.0937 0.4993 0.9338
4.250 0.9329 0.00757 0.00305 -0.0936 0.4964 0.9407
4.500 0.9589 0.00756 0.00308 -0.0931 0.4927 0.9477
4.750 0.9842 0.00760 0.00312 -0.0926 0.4882 0.9558
5.000 1.0085 0.00762 0.00316 -0.0919 0.4839 0.9650
5.250 1.0347 0.00759 0.00319 -0.0915 0.4799 0.9758
5.500 1.0652 0.00762 0.00323 -0.0922 0.4755 0.9894
5.750 1.0957 0.00773 0.00332 -0.0930 0.4704 1.0000
6.000 1.1261 0.00777 0.00341 -0.0938 0.4654 1.0000
6.250 1.1555 0.00787 0.00351 -0.0943 0.4588 1.0000
6.500 1.1847 0.00798 0.00363 -0.0948 0.4529 1.0000
6.750 1.2138 0.00808 0.00375 -0.0953 0.4460 1.0000
7.000 1.2422 0.00821 0.00389 -0.0956 0.4380 1.0000
7.250 1.2698 0.00839 0.00404 -0.0958 0.4247 1.0000
7.500 1.2968 0.00860 0.00421 -0.0960 0.4075 1.0000
7.750 1.3216 0.00897 0.00448 -0.0957 0.3814 1.0000
8.000 1.3438 0.00954 0.00487 -0.0951 0.3431 1.0000
8.250 1.3613 0.01045 0.00551 -0.0938 0.2930 1.0000
8.500 1.3764 0.01150 0.00627 -0.0921 0.2415 1.0000
8.750 1.3911 0.01251 0.00704 -0.0904 0.1989 1.0000
9.000 1.4060 0.01343 0.00777 -0.0887 0.1658 1.0000
9.250 1.4207 0.01429 0.00849 -0.0870 0.1387 1.0000
9.500 1.4345 0.01514 0.00921 -0.0852 0.1162 1.0000
9.750 1.4454 0.01603 0.00999 -0.0829 0.0969 1.0000
10.000 1.4540 0.01688 0.01077 -0.0801 0.0821 1.0000
10.250 1.4620 0.01782 0.01166 -0.0775 0.0692 1.0000
10.500 1.4692 0.01888 0.01268 -0.0751 0.0584 1.0000
10.750 1.4756 0.02009 0.01387 -0.0729 0.0494 1.0000
11.000 1.4811 0.02153 0.01529 -0.0710 0.0417 1.0000
11.500 1.4920 0.02500 0.01877 -0.0685 0.0298 1.0000
11.750 1.4974 0.02696 0.02076 -0.0676 0.0257 1.0000
12.000 1.5014 0.02915 0.02297 -0.0668 0.0224 1.0000
12.250 1.5062 0.03128 0.02514 -0.0662 0.0203 1.0000
12.500 1.5081 0.03372 0.02762 -0.0654 0.0182 1.0000
12.750 1.5134 0.03582 0.02979 -0.0649 0.0171 1.0000
13.000 1.5155 0.03822 0.03223 -0.0642 0.0159 1.0000
13.250 1.5138 0.04101 0.03506 -0.0634 0.0147 1.0000
13.500 1.5180 0.04322 0.03734 -0.0628 0.0142 1.0000
13.750 1.5203 0.04558 0.03977 -0.0622 0.0136 1.0000
14.000 1.5214 0.04809 0.04234 -0.0616 0.0130 1.0000
14.250 1.5216 0.05075 0.04505 -0.0610 0.0125 1.0000
14.500 1.5190 0.05375 0.04811 -0.0605 0.0119 1.0000
14.750 1.5159 0.05690 0.05134 -0.0600 0.0115 1.0000
15.000 1.5187 0.05945 0.05396 -0.0598 0.0113 1.0000
15.250 1.5208 0.06208 0.05666 -0.0595 0.0110 1.0000
15.500 1.5214 0.06493 0.05957 -0.0593 0.0107 1.0000
15.750 1.5223 0.06776 0.06248 -0.0592 0.0104 1.0000
16.000 1.5227 0.07072 0.06550 -0.0591 0.0101 1.0000
16.250 1.5222 0.07381 0.06865 -0.0591 0.0099 1.0000
16.500 1.5199 0.07711 0.07202 -0.0591 0.0096 1.0000
16.750 1.5145 0.08091 0.07588 -0.0593 0.0093 1.0000
17.000 1.5052 0.08526 0.08033 -0.0596 0.0090 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 93-W-145 (ah93w145-il)