AH 93-W-174 (ah93w174-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-174 (ah93w174-il) Reynolds number: 100,000 Max Cl/Cd: 33 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w174-il-100000-n5.txt Download as CSV file: xf-ah93w174-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-174
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4846 0.07884 0.07374 -0.0702 0.9468 0.0528
-12.250 -0.5686 0.05820 0.05257 -0.0905 0.8988 0.0520
-12.000 -0.5923 0.04971 0.04340 -0.1007 0.8554 0.0525
-11.750 -0.6099 0.04533 0.03846 -0.1032 0.8246 0.0532
-11.500 -0.5983 0.04388 0.03691 -0.1033 0.8039 0.0542
-11.250 -0.5938 0.04233 0.03519 -0.1028 0.7873 0.0552
-11.000 -0.5932 0.04074 0.03339 -0.1014 0.7734 0.0561
-10.750 -0.5900 0.03907 0.03149 -0.1001 0.7618 0.0572
-10.500 -0.5843 0.03737 0.02948 -0.0989 0.7524 0.0587
-10.250 -0.5776 0.03562 0.02735 -0.0977 0.7429 0.0606
-10.000 -0.5631 0.03433 0.02588 -0.0969 0.7355 0.0623
-9.750 -0.5457 0.03341 0.02492 -0.0963 0.7274 0.0641
-9.500 -0.5284 0.03234 0.02368 -0.0956 0.7205 0.0661
-9.250 -0.5108 0.03119 0.02227 -0.0949 0.7139 0.0687
-9.000 -0.4923 0.03008 0.02093 -0.0942 0.7072 0.0713
-8.750 -0.4717 0.02934 0.02016 -0.0937 0.7017 0.0738
-8.500 -0.4510 0.02853 0.01923 -0.0931 0.6960 0.0767
-8.250 -0.4299 0.02769 0.01815 -0.0926 0.6906 0.0803
-8.000 -0.4084 0.02694 0.01737 -0.0921 0.6857 0.0836
-7.750 -0.3862 0.02633 0.01667 -0.0916 0.6814 0.0875
-7.500 -0.3636 0.02568 0.01585 -0.0910 0.6760 0.0920
-7.250 -0.3415 0.02505 0.01522 -0.0905 0.6711 0.0963
-7.000 -0.3184 0.02453 0.01460 -0.0900 0.6670 0.1016
-6.750 -0.2951 0.02398 0.01395 -0.0896 0.6632 0.1072
-6.500 -0.2722 0.02353 0.01351 -0.0891 0.6588 0.1134
-6.250 -0.2485 0.02308 0.01297 -0.0887 0.6547 0.1205
-6.000 -0.2250 0.02265 0.01253 -0.0882 0.6510 0.1281
-5.750 -0.2007 0.02224 0.01204 -0.0878 0.6478 0.1367
-5.500 -0.1771 0.02190 0.01170 -0.0874 0.6437 0.1467
-5.250 -0.1535 0.02154 0.01138 -0.0870 0.6396 0.1573
-5.000 -0.1292 0.02122 0.01105 -0.0866 0.6361 0.1699
-4.750 -0.1044 0.02092 0.01072 -0.0863 0.6331 0.1845
-4.500 -0.0792 0.02063 0.01042 -0.0860 0.6305 0.2011
-4.250 -0.0552 0.02037 0.01024 -0.0856 0.6269 0.2201
-4.000 -0.0311 0.02013 0.01008 -0.0853 0.6231 0.2422
-3.750 -0.0065 0.01988 0.00990 -0.0850 0.6196 0.2687
-3.500 0.0184 0.01962 0.00972 -0.0847 0.6166 0.3003
-3.250 0.0436 0.01937 0.00956 -0.0844 0.6141 0.3380
-3.000 0.0683 0.01916 0.00951 -0.0840 0.6116 0.3827
-2.750 0.0916 0.01903 0.00961 -0.0834 0.6081 0.4314
-2.500 0.1154 0.01895 0.00973 -0.0828 0.6047 0.4822
-2.250 0.1400 0.01893 0.00983 -0.0820 0.6016 0.5301
-2.000 0.1650 0.01896 0.00994 -0.0813 0.5988 0.5717
-1.750 0.1907 0.01904 0.01004 -0.0805 0.5966 0.6074
-1.500 0.2158 0.01921 0.01022 -0.0798 0.5942 0.6377
-1.250 0.2387 0.01946 0.01054 -0.0788 0.5908 0.6632
-1.000 0.2628 0.01968 0.01077 -0.0780 0.5876 0.6874
-0.750 0.2869 0.01988 0.01097 -0.0770 0.5846 0.7079
-0.500 0.3116 0.02005 0.01111 -0.0761 0.5820 0.7271
-0.250 0.3368 0.02022 0.01122 -0.0753 0.5798 0.7452
0.000 0.3623 0.02040 0.01133 -0.0745 0.5780 0.7622
0.250 0.3823 0.02077 0.01178 -0.0732 0.5745 0.7784
0.500 0.4034 0.02107 0.01212 -0.0719 0.5711 0.7945
0.750 0.4251 0.02130 0.01235 -0.0706 0.5681 0.8096
1.000 0.4476 0.02146 0.01250 -0.0693 0.5655 0.8238
1.250 0.4714 0.02159 0.01259 -0.0682 0.5634 0.8371
1.500 0.4962 0.02171 0.01266 -0.0675 0.5617 0.8500
1.750 0.5156 0.02206 0.01306 -0.0662 0.5586 0.8632
2.000 0.5333 0.02244 0.01351 -0.0647 0.5548 0.8753
2.250 0.5544 0.02267 0.01377 -0.0636 0.5516 0.8874
2.500 0.5782 0.02282 0.01392 -0.0629 0.5491 0.8998
2.750 0.6038 0.02294 0.01401 -0.0625 0.5470 0.9122
3.000 0.6328 0.02303 0.01407 -0.0628 0.5453 0.9239
3.250 0.6580 0.02340 0.01450 -0.0628 0.5422 0.9365
3.500 0.6815 0.02404 0.01526 -0.0631 0.5377 0.9507
3.750 0.7147 0.02443 0.01569 -0.0649 0.5345 0.9632
4.000 0.7523 0.02472 0.01599 -0.0673 0.5320 0.9761
4.500 0.8189 0.02501 0.01621 -0.0702 0.5282 1.0000
4.750 0.8225 0.02616 0.01748 -0.0678 0.5231 1.0000
5.000 0.8361 0.02705 0.01845 -0.0667 0.5190 1.0000
5.250 0.8591 0.02750 0.01891 -0.0666 0.5161 1.0000
5.500 0.8869 0.02771 0.01911 -0.0669 0.5139 1.0000
5.750 0.9176 0.02781 0.01919 -0.0675 0.5122 1.0000
6.250 0.9231 0.03086 0.02245 -0.0632 0.5012 1.0000
6.500 0.9485 0.03115 0.02276 -0.0632 0.4986 1.0000
6.750 0.9786 0.03123 0.02286 -0.0636 0.4968 1.0000
7.000 1.0117 0.03119 0.02282 -0.0643 0.4953 1.0000
7.500 0.9808 0.03574 0.02756 -0.0565 0.4813 1.0000
7.750 1.0156 0.03546 0.02732 -0.0571 0.4800 1.0000
8.000 1.0546 0.03497 0.02686 -0.0581 0.4788 1.0000
8.500 1.0151 0.04090 0.03292 -0.0519 0.4628 1.0000
9.500 1.0019 0.05134 0.04358 -0.0481 0.4316 1.0000
10.000 1.0003 0.05650 0.04886 -0.0470 0.4153 1.0000
10.500 1.0171 0.05969 0.05218 -0.0460 0.4020 1.0000
11.250 1.0584 0.06259 0.05531 -0.0447 0.3851 1.0000
11.750 1.0687 0.06646 0.05933 -0.0440 0.3689 1.0000
12.250 1.0993 0.06781 0.06086 -0.0431 0.3560 1.0000
12.750 1.0946 0.07373 0.06693 -0.0430 0.3340 1.0000
13.000 1.1168 0.07349 0.06679 -0.0425 0.3278 1.0000
13.500 1.1503 0.07452 0.06797 -0.0418 0.3111 1.0000
13.750 1.1511 0.07727 0.07079 -0.0419 0.2985 1.0000
14.000 1.1616 0.07874 0.07231 -0.0418 0.2871 1.0000
14.250 1.1811 0.07890 0.07250 -0.0414 0.2759 1.0000
14.500 1.1981 0.07942 0.07302 -0.0411 0.2630 1.0000
14.750 1.2084 0.08089 0.07447 -0.0409 0.2483 1.0000
15.000 1.2154 0.08286 0.07640 -0.0410 0.2328 1.0000
15.250 1.2196 0.08527 0.07876 -0.0411 0.2168 1.0000
15.500 1.2217 0.08802 0.08147 -0.0414 0.2008 1.0000
15.750 1.2220 0.09111 0.08450 -0.0419 0.1853 1.0000
16.000 1.2208 0.09449 0.08782 -0.0425 0.1703 1.0000
16.250 1.2188 0.09805 0.09134 -0.0433 0.1563 1.0000
16.500 1.2161 0.10179 0.09502 -0.0442 0.1432 1.0000
16.750 1.2133 0.10562 0.09881 -0.0453 0.1311 1.0000
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Polar data table (+)
Polar graphs
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