AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.86 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w145-il-1000000-n5.txt Download as CSV file: xf-ah93w145-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7724 0.10307 0.10076 -0.0383 1.0000 0.0092
-16.000 -0.8674 0.08285 0.08037 -0.0502 1.0000 0.0090
-15.750 -1.0489 0.04496 0.04189 -0.0775 1.0000 0.0086
-15.500 -1.0680 0.03827 0.03500 -0.0832 1.0000 0.0086
-15.250 -1.0755 0.03446 0.03104 -0.0854 1.0000 0.0087
-15.000 -1.0791 0.03178 0.02824 -0.0860 1.0000 0.0087
-14.750 -1.0813 0.02979 0.02613 -0.0852 1.0000 0.0088
-14.500 -1.0858 0.02831 0.02455 -0.0827 1.0000 0.0089
-14.250 -1.0836 0.02707 0.02322 -0.0805 1.0000 0.0089
-14.000 -1.0663 0.02579 0.02184 -0.0807 0.9960 0.0090
-13.750 -1.0434 0.02460 0.02053 -0.0817 0.9859 0.0091
-13.500 -0.9926 0.02268 0.01837 -0.0891 0.9161 0.0095
-13.250 -0.9772 0.02202 0.01729 -0.0879 0.8217 0.0097
-13.000 -0.9587 0.02130 0.01636 -0.0872 0.7879 0.0099
-12.750 -0.9383 0.02062 0.01553 -0.0868 0.7633 0.0101
-12.500 -0.9170 0.01999 0.01475 -0.0864 0.7424 0.0103
-12.250 -0.8948 0.01939 0.01402 -0.0861 0.7246 0.0105
-12.000 -0.8719 0.01882 0.01333 -0.0858 0.7085 0.0107
-11.750 -0.8485 0.01828 0.01266 -0.0856 0.6938 0.0110
-11.500 -0.8246 0.01776 0.01202 -0.0854 0.6807 0.0112
-11.250 -0.8003 0.01727 0.01141 -0.0852 0.6693 0.0115
-10.750 -0.7505 0.01633 0.01027 -0.0849 0.6507 0.0119
-10.250 -0.7000 0.01534 0.00913 -0.0848 0.6355 0.0128
-10.000 -0.6741 0.01497 0.00869 -0.0847 0.6281 0.0133
-9.750 -0.6477 0.01461 0.00826 -0.0847 0.6220 0.0138
-9.500 -0.6212 0.01426 0.00784 -0.0847 0.6159 0.0143
-9.250 -0.5945 0.01394 0.00744 -0.0847 0.6107 0.0146
-9.000 -0.5676 0.01360 0.00704 -0.0848 0.6064 0.0150
-8.750 -0.5408 0.01322 0.00661 -0.0848 0.6019 0.0158
-8.500 -0.5137 0.01291 0.00626 -0.0849 0.5973 0.0165
-8.250 -0.4863 0.01263 0.00593 -0.0849 0.5933 0.0172
-8.000 -0.4587 0.01238 0.00563 -0.0850 0.5894 0.0180
-7.750 -0.4310 0.01213 0.00533 -0.0851 0.5853 0.0188
-7.500 -0.4035 0.01185 0.00502 -0.0852 0.5815 0.0200
-7.250 -0.3756 0.01162 0.00476 -0.0854 0.5783 0.0212
-7.000 -0.3475 0.01140 0.00451 -0.0855 0.5756 0.0223
-6.750 -0.3194 0.01118 0.00425 -0.0857 0.5725 0.0236
-6.500 -0.2913 0.01096 0.00402 -0.0858 0.5693 0.0254
-6.250 -0.2630 0.01079 0.00382 -0.0860 0.5660 0.0272
-6.000 -0.2348 0.01061 0.00361 -0.0862 0.5629 0.0293
-5.750 -0.2063 0.01042 0.00342 -0.0864 0.5604 0.0317
-5.500 -0.1777 0.01028 0.00325 -0.0866 0.5578 0.0335
-5.250 -0.1492 0.01010 0.00307 -0.0868 0.5551 0.0367
-5.000 -0.1205 0.00996 0.00292 -0.0870 0.5525 0.0397
-4.750 -0.0920 0.00982 0.00277 -0.0872 0.5499 0.0433
-4.500 -0.0633 0.00970 0.00263 -0.0874 0.5472 0.0471
-4.250 -0.0344 0.00956 0.00250 -0.0877 0.5450 0.0516
-4.000 -0.0055 0.00943 0.00239 -0.0880 0.5426 0.0566
-3.750 0.0233 0.00930 0.00227 -0.0882 0.5402 0.0628
-3.500 0.0523 0.00920 0.00217 -0.0885 0.5379 0.0693
-3.250 0.0811 0.00908 0.00207 -0.0888 0.5356 0.0786
-3.000 0.1100 0.00898 0.00199 -0.0890 0.5332 0.0881
-2.750 0.1389 0.00888 0.00191 -0.0893 0.5311 0.1002
-2.500 0.1680 0.00877 0.00184 -0.0896 0.5291 0.1137
-2.250 0.1971 0.00865 0.00178 -0.0900 0.5268 0.1307
-2.000 0.2262 0.00854 0.00172 -0.0903 0.5246 0.1493
-1.750 0.2553 0.00845 0.00168 -0.0906 0.5224 0.1702
-1.500 0.2843 0.00833 0.00164 -0.0910 0.5203 0.1955
-1.250 0.3133 0.00823 0.00160 -0.0913 0.5181 0.2258
-1.000 0.3423 0.00808 0.00157 -0.0917 0.5159 0.2694
-0.750 0.3716 0.00787 0.00155 -0.0922 0.5141 0.3292
-0.500 0.4008 0.00764 0.00153 -0.0927 0.5120 0.4001
-0.250 0.4301 0.00745 0.00153 -0.0932 0.5099 0.4673
0.000 0.4593 0.00730 0.00154 -0.0936 0.5079 0.5275
0.250 0.4885 0.00717 0.00157 -0.0940 0.5057 0.5822
0.500 0.5176 0.00708 0.00160 -0.0944 0.5035 0.6314
0.750 0.5465 0.00705 0.00165 -0.0947 0.5011 0.6677
1.000 0.5758 0.00701 0.00169 -0.0950 0.4994 0.6974
1.250 0.6048 0.00698 0.00175 -0.0953 0.4976 0.7269
1.500 0.6338 0.00697 0.00181 -0.0955 0.4956 0.7543
1.750 0.6621 0.00695 0.00190 -0.0956 0.4933 0.7909
2.000 0.6904 0.00697 0.00198 -0.0957 0.4909 0.8160
2.250 0.7189 0.00702 0.00204 -0.0958 0.4886 0.8272
2.500 0.7473 0.00708 0.00211 -0.0960 0.4863 0.8369
2.750 0.7760 0.00712 0.00219 -0.0961 0.4844 0.8456
3.000 0.8048 0.00717 0.00226 -0.0964 0.4821 0.8531
3.250 0.8332 0.00721 0.00233 -0.0965 0.4797 0.8605
3.500 0.8618 0.00728 0.00241 -0.0967 0.4770 0.8675
3.750 0.8898 0.00734 0.00249 -0.0968 0.4744 0.8739
4.000 0.9178 0.00743 0.00258 -0.0969 0.4714 0.8805
4.250 0.9461 0.00748 0.00267 -0.0970 0.4681 0.8863
4.500 0.9741 0.00753 0.00275 -0.0971 0.4627 0.8925
4.750 1.0017 0.00765 0.00285 -0.0972 0.4559 0.8986
5.000 1.0292 0.00770 0.00294 -0.0971 0.4495 0.9042
5.250 1.0565 0.00781 0.00304 -0.0971 0.4432 0.9104
5.500 1.0839 0.00790 0.00316 -0.0971 0.4369 0.9159
5.750 1.1103 0.00802 0.00328 -0.0969 0.4281 0.9218
6.000 1.1371 0.00814 0.00341 -0.0969 0.4182 0.9280
6.250 1.1622 0.00831 0.00356 -0.0964 0.4042 0.9343
6.500 1.1871 0.00852 0.00374 -0.0960 0.3890 0.9418
6.750 1.2101 0.00879 0.00395 -0.0952 0.3695 0.9504
7.000 1.2308 0.00921 0.00426 -0.0941 0.3394 0.9622
7.250 1.2485 0.01005 0.00481 -0.0927 0.2840 0.9908
7.500 1.2650 0.01110 0.00554 -0.0913 0.2278 1.0000
7.750 1.2820 0.01204 0.00623 -0.0899 0.1836 1.0000
8.000 1.2992 0.01290 0.00689 -0.0886 0.1491 1.0000
8.250 1.3172 0.01364 0.00749 -0.0874 0.1233 1.0000
8.500 1.3356 0.01430 0.00806 -0.0863 0.1038 1.0000
8.750 1.3523 0.01502 0.00868 -0.0848 0.0859 1.0000
9.000 1.3684 0.01573 0.00931 -0.0833 0.0718 1.0000
9.250 1.3830 0.01640 0.00994 -0.0816 0.0611 1.0000
9.500 1.3958 0.01707 0.01058 -0.0795 0.0528 1.0000
9.750 1.4083 0.01779 0.01129 -0.0775 0.0458 1.0000
10.000 1.4195 0.01863 0.01212 -0.0755 0.0396 1.0000
10.250 1.4293 0.01961 0.01308 -0.0735 0.0337 1.0000
10.500 1.4382 0.02073 0.01422 -0.0717 0.0286 1.0000
10.750 1.4479 0.02194 0.01545 -0.0704 0.0249 1.0000
11.000 1.4566 0.02337 0.01689 -0.0692 0.0217 1.0000
11.250 1.4656 0.02491 0.01846 -0.0684 0.0194 1.0000
11.500 1.4745 0.02655 0.02014 -0.0677 0.0176 1.0000
11.750 1.4830 0.02828 0.02192 -0.0671 0.0161 1.0000
12.000 1.4898 0.03022 0.02389 -0.0665 0.0146 1.0000
12.250 1.4976 0.03208 0.02580 -0.0660 0.0137 1.0000
12.500 1.5036 0.03411 0.02788 -0.0654 0.0127 1.0000
12.750 1.5082 0.03628 0.03010 -0.0648 0.0119 1.0000
13.000 1.5132 0.03840 0.03227 -0.0642 0.0112 1.0000
13.250 1.5177 0.04057 0.03449 -0.0637 0.0106 1.0000
13.500 1.5211 0.04285 0.03683 -0.0631 0.0101 1.0000
13.750 1.5233 0.04522 0.03924 -0.0625 0.0096 1.0000
14.000 1.5246 0.04769 0.04177 -0.0618 0.0091 1.0000
14.250 1.5274 0.05006 0.04420 -0.0613 0.0089 1.0000
14.500 1.5302 0.05248 0.04668 -0.0609 0.0086 1.0000
14.750 1.5327 0.05496 0.04923 -0.0605 0.0083 1.0000
15.000 1.5354 0.05746 0.05178 -0.0602 0.0081 1.0000
15.250 1.5372 0.06012 0.05450 -0.0599 0.0078 1.0000
15.500 1.5390 0.06276 0.05720 -0.0597 0.0076 1.0000
15.750 1.5400 0.06556 0.06006 -0.0595 0.0074 1.0000
16.000 1.5403 0.06845 0.06301 -0.0594 0.0071 1.0000
16.250 1.5400 0.07147 0.06609 -0.0593 0.0069 1.0000
16.500 1.5407 0.07441 0.06910 -0.0593 0.0068 1.0000
16.750 1.5421 0.07724 0.07200 -0.0593 0.0066 1.0000
17.000 1.5425 0.08026 0.07509 -0.0594 0.0065 1.0000
17.250 1.5433 0.08324 0.07813 -0.0596 0.0064 1.0000
17.500 1.5429 0.08642 0.08139 -0.0598 0.0062 1.0000
17.750 1.5429 0.08956 0.08460 -0.0601 0.0061 1.0000
18.000 1.5413 0.09292 0.08804 -0.0605 0.0059 1.0000
18.250 1.5403 0.09623 0.09141 -0.0609 0.0058 1.0000
18.500 1.5377 0.09981 0.09507 -0.0615 0.0057 1.0000
18.750 1.5354 0.10338 0.09870 -0.0621 0.0056 1.0000
19.000 1.5323 0.10710 0.10250 -0.0628 0.0055 1.0000
19.250 1.5282 0.11099 0.10647 -0.0637 0.0054 1.0000
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Polar data table (+)
Polar graphs
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