AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 500,000 Max Cl/Cd: 120.21 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w145-il-500000.txt Download as CSV file: xf-ah93w145-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6812 0.05450 0.05170 -0.0732 1.0000 0.0185
-12.250 -0.7067 0.04691 0.04390 -0.0801 1.0000 0.0185
-12.000 -0.7301 0.04211 0.03890 -0.0823 1.0000 0.0185
-11.750 -0.7536 0.03925 0.03589 -0.0801 1.0000 0.0185
-11.250 -0.7853 0.03265 0.02879 -0.0751 0.9990 0.0188
-11.000 -0.7596 0.02967 0.02560 -0.0785 0.9882 0.0192
-10.750 -0.7271 0.02803 0.02385 -0.0816 0.9682 0.0198
-10.500 -0.6766 0.02612 0.02169 -0.0884 0.9251 0.0206
-10.250 -0.6434 0.02481 0.01993 -0.0908 0.8541 0.0214
-10.000 -0.6249 0.02384 0.01858 -0.0899 0.8134 0.0221
-9.750 -0.6045 0.02303 0.01743 -0.0892 0.7855 0.0226
-9.500 -0.5871 0.02111 0.01520 -0.0885 0.7639 0.0233
-9.250 -0.5650 0.02025 0.01420 -0.0881 0.7455 0.0240
-9.000 -0.5413 0.01966 0.01347 -0.0878 0.7300 0.0247
-8.750 -0.5171 0.01903 0.01269 -0.0876 0.7169 0.0256
-8.500 -0.4925 0.01843 0.01190 -0.0873 0.7058 0.0266
-8.250 -0.4666 0.01802 0.01132 -0.0871 0.6958 0.0275
-8.000 -0.4434 0.01687 0.01007 -0.0869 0.6877 0.0290
-7.750 -0.4175 0.01644 0.00958 -0.0868 0.6796 0.0303
-7.500 -0.3913 0.01601 0.00904 -0.0867 0.6728 0.0317
-7.250 -0.3645 0.01562 0.00853 -0.0866 0.6658 0.0331
-7.000 -0.3395 0.01484 0.00767 -0.0865 0.6599 0.0351
-6.750 -0.3124 0.01453 0.00734 -0.0865 0.6544 0.0373
-6.500 -0.2849 0.01426 0.00699 -0.0866 0.6490 0.0396
-6.250 -0.2587 0.01370 0.00633 -0.0865 0.6444 0.0423
-6.000 -0.2313 0.01339 0.00601 -0.0866 0.6400 0.0453
-5.750 -0.2032 0.01319 0.00575 -0.0867 0.6354 0.0484
-5.500 -0.1763 0.01273 0.00527 -0.0867 0.6311 0.0528
-5.250 -0.1484 0.01258 0.00503 -0.0868 0.6270 0.0570
-5.000 -0.1206 0.01222 0.00467 -0.0870 0.6233 0.0623
-4.750 -0.0924 0.01202 0.00447 -0.0871 0.6195 0.0679
-4.500 -0.0644 0.01174 0.00417 -0.0873 0.6161 0.0749
-4.250 -0.0360 0.01162 0.00399 -0.0875 0.6128 0.0821
-4.000 -0.0078 0.01138 0.00378 -0.0877 0.6095 0.0933
-3.750 0.0206 0.01115 0.00359 -0.0879 0.6062 0.1069
-3.500 0.0491 0.01095 0.00344 -0.0882 0.6029 0.1244
-3.250 0.0775 0.01073 0.00329 -0.0885 0.5998 0.1484
-3.000 0.1060 0.01056 0.00318 -0.0888 0.5969 0.1777
-2.750 0.1346 0.01038 0.00310 -0.0891 0.5942 0.2159
-2.500 0.1631 0.01009 0.00301 -0.0895 0.5915 0.2695
-2.250 0.1915 0.00970 0.00292 -0.0900 0.5886 0.3557
-2.000 0.2197 0.00928 0.00287 -0.0904 0.5857 0.4668
-1.750 0.2480 0.00899 0.00286 -0.0907 0.5830 0.5623
-1.500 0.2763 0.00885 0.00290 -0.0909 0.5804 0.6362
-1.250 0.3044 0.00879 0.00298 -0.0909 0.5780 0.6913
-1.000 0.3323 0.00873 0.00305 -0.0908 0.5756 0.7338
-0.750 0.3601 0.00873 0.00312 -0.0907 0.5730 0.7661
-0.500 0.3878 0.00876 0.00318 -0.0905 0.5703 0.7912
-0.250 0.4154 0.00881 0.00324 -0.0903 0.5678 0.8126
0.000 0.4429 0.00890 0.00332 -0.0901 0.5655 0.8315
0.250 0.4703 0.00906 0.00344 -0.0898 0.5630 0.8467
0.500 0.4972 0.00910 0.00352 -0.0895 0.5610 0.8599
0.750 0.5239 0.00915 0.00361 -0.0891 0.5586 0.8726
1.000 0.5503 0.00922 0.00369 -0.0887 0.5560 0.8856
1.250 0.5738 0.00929 0.00377 -0.0874 0.5536 0.9019
1.500 0.5962 0.00935 0.00384 -0.0860 0.5514 0.9173
1.750 0.6211 0.00944 0.00391 -0.0852 0.5493 0.9284
2.000 0.6443 0.00954 0.00399 -0.0841 0.5471 0.9379
2.250 0.6681 0.00951 0.00402 -0.0831 0.5449 0.9479
2.500 0.6924 0.00951 0.00404 -0.0823 0.5424 0.9584
2.750 0.7181 0.00950 0.00406 -0.0818 0.5400 0.9688
3.000 0.7490 0.00952 0.00408 -0.0825 0.5376 0.9778
3.250 0.7834 0.00958 0.00412 -0.0840 0.5352 0.9857
3.500 0.8197 0.00971 0.00421 -0.0860 0.5328 0.9933
3.750 0.8536 0.00982 0.00435 -0.0875 0.5304 1.0000
4.000 0.8813 0.00991 0.00448 -0.0878 0.5277 1.0000
4.250 0.9103 0.01000 0.00460 -0.0883 0.5250 1.0000
4.500 0.9398 0.01010 0.00471 -0.0890 0.5223 1.0000
4.750 0.9696 0.01020 0.00481 -0.0896 0.5195 1.0000
5.000 0.9995 0.01040 0.00496 -0.0903 0.5162 1.0000
5.250 1.0280 0.01040 0.00506 -0.0906 0.5121 1.0000
5.500 1.0569 0.01041 0.00510 -0.0910 0.5071 1.0000
5.750 1.0859 0.01047 0.00514 -0.0914 0.5026 1.0000
6.000 1.1143 0.01057 0.00528 -0.0917 0.4982 1.0000
6.250 1.1425 0.01060 0.00538 -0.0920 0.4930 1.0000
6.500 1.1707 0.01065 0.00543 -0.0922 0.4879 1.0000
6.750 1.1983 0.01072 0.00556 -0.0924 0.4819 1.0000
7.000 1.2258 0.01075 0.00564 -0.0924 0.4753 1.0000
7.250 1.2531 0.01086 0.00577 -0.0925 0.4692 1.0000
7.500 1.2801 0.01092 0.00591 -0.0926 0.4615 1.0000
7.750 1.3064 0.01101 0.00603 -0.0925 0.4516 1.0000
8.000 1.3320 0.01112 0.00617 -0.0922 0.4390 1.0000
8.250 1.3572 0.01129 0.00635 -0.0920 0.4240 1.0000
8.500 1.3811 0.01154 0.00659 -0.0915 0.4029 1.0000
8.750 1.4020 0.01199 0.00694 -0.0906 0.3725 1.0000
9.000 1.4171 0.01282 0.00755 -0.0889 0.3274 1.0000
9.250 1.4259 0.01406 0.00850 -0.0863 0.2751 1.0000
9.500 1.4322 0.01540 0.00958 -0.0834 0.2294 1.0000
9.750 1.4363 0.01673 0.01069 -0.0802 0.1927 1.0000
10.000 1.4377 0.01798 0.01180 -0.0766 0.1646 1.0000
10.250 1.4395 0.01933 0.01305 -0.0734 0.1405 1.0000
10.500 1.4402 0.02089 0.01452 -0.0706 0.1207 1.0000
10.750 1.4416 0.02262 0.01620 -0.0684 0.1035 1.0000
11.000 1.4423 0.02468 0.01822 -0.0667 0.0889 1.0000
11.250 1.4428 0.02700 0.02052 -0.0656 0.0761 1.0000
11.500 1.4428 0.02952 0.02302 -0.0646 0.0650 1.0000
11.750 1.4421 0.03219 0.02568 -0.0638 0.0554 1.0000
12.000 1.4407 0.03497 0.02845 -0.0630 0.0472 1.0000
12.250 1.4383 0.03784 0.03134 -0.0622 0.0406 1.0000
12.500 1.4349 0.04081 0.03431 -0.0614 0.0355 1.0000
12.750 1.4343 0.04352 0.03707 -0.0607 0.0317 1.0000
13.000 1.4295 0.04664 0.04020 -0.0599 0.0287 1.0000
13.250 1.4293 0.04931 0.04295 -0.0593 0.0266 1.0000
13.500 1.4277 0.05217 0.04587 -0.0587 0.0248 1.0000
13.750 1.4221 0.05554 0.04928 -0.0581 0.0233 1.0000
14.000 1.4215 0.05846 0.05228 -0.0577 0.0221 1.0000
14.250 1.4220 0.06130 0.05520 -0.0574 0.0211 1.0000
14.500 1.4216 0.06428 0.05824 -0.0572 0.0201 1.0000
14.750 1.4186 0.06759 0.06162 -0.0570 0.0193 1.0000
15.000 1.4100 0.07166 0.06574 -0.0569 0.0185 1.0000
15.250 1.4116 0.07456 0.06873 -0.0569 0.0179 1.0000
15.500 1.4127 0.07750 0.07176 -0.0569 0.0173 1.0000
15.750 1.4124 0.08068 0.07502 -0.0570 0.0167 1.0000
16.000 1.4121 0.08388 0.07829 -0.0572 0.0162 1.0000
16.250 1.4102 0.08734 0.08181 -0.0574 0.0157 1.0000
16.500 1.4064 0.09103 0.08555 -0.0577 0.0153 1.0000
16.750 1.4001 0.09503 0.08961 -0.0581 0.0149 1.0000
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Polar data table (+)
Polar graphs
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