AH 93-157 (ah93157-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-157 (ah93157-il) Reynolds number: 100,000 Max Cl/Cd: 37.47 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93157-il-100000-n5.txt Download as CSV file: xf-ah93157-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-157
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2263 0.10107 0.09584 -0.0931 0.9232 0.0345
-11.750 -0.2260 0.09536 0.09011 -0.0972 0.9170 0.0346
-11.500 -0.2308 0.08836 0.08309 -0.1023 0.9115 0.0347
-11.250 -0.2402 0.08115 0.07588 -0.1070 0.9048 0.0348
-11.000 -0.2572 0.07152 0.06621 -0.1142 0.8983 0.0347
-10.750 -0.2729 0.06502 0.05962 -0.1193 0.8917 0.0344
-10.500 -0.2988 0.05947 0.05391 -0.1219 0.8841 0.0342
-10.250 -0.3213 0.05537 0.04961 -0.1218 0.8775 0.0341
-10.000 -0.3454 0.05215 0.04619 -0.1192 0.8697 0.0341
-9.750 -0.3667 0.04929 0.04304 -0.1157 0.8639 0.0342
-9.500 -0.3821 0.04652 0.03995 -0.1121 0.8580 0.0344
-9.250 -0.3930 0.04366 0.03667 -0.1085 0.8526 0.0346
-9.000 -0.3938 0.04113 0.03377 -0.1057 0.8486 0.0350
-8.750 -0.3870 0.03946 0.03192 -0.1036 0.8441 0.0355
-8.500 -0.3774 0.03812 0.03042 -0.1017 0.8395 0.0363
-8.250 -0.3649 0.03689 0.02899 -0.1001 0.8359 0.0375
-8.000 -0.3515 0.03536 0.02714 -0.0984 0.8328 0.0392
-7.750 -0.3395 0.03373 0.02512 -0.0963 0.8288 0.0408
-7.500 -0.3256 0.03217 0.02313 -0.0943 0.8244 0.0420
-7.250 -0.3063 0.03086 0.02173 -0.0934 0.8210 0.0433
-7.000 -0.2849 0.02998 0.02073 -0.0927 0.8182 0.0453
-6.750 -0.2616 0.02903 0.01956 -0.0921 0.8158 0.0484
-6.500 -0.2437 0.02825 0.01855 -0.0906 0.8111 0.0506
-6.250 -0.2231 0.02734 0.01764 -0.0897 0.8074 0.0527
-6.000 -0.2010 0.02672 0.01697 -0.0890 0.8043 0.0561
-5.750 -0.1762 0.02604 0.01610 -0.0885 0.8017 0.0607
-5.500 -0.1523 0.02524 0.01531 -0.0880 0.7994 0.0645
-5.250 -0.1382 0.02505 0.01512 -0.0860 0.7941 0.0693
-5.000 -0.1187 0.02460 0.01461 -0.0847 0.7903 0.0751
-4.750 -0.0969 0.02413 0.01413 -0.0838 0.7872 0.0825
-4.500 -0.0737 0.02361 0.01359 -0.0831 0.7848 0.0922
-4.250 -0.0570 0.02340 0.01339 -0.0814 0.7807 0.1032
-4.000 -0.0419 0.02325 0.01328 -0.0794 0.7758 0.1170
-3.750 -0.0213 0.02287 0.01299 -0.0783 0.7723 0.1389
-3.500 0.0021 0.02240 0.01266 -0.0777 0.7698 0.1763
-3.250 0.0261 0.02180 0.01236 -0.0772 0.7678 0.2455
-3.000 0.0307 0.02178 0.01274 -0.0737 0.7608 0.3255
-2.750 0.0416 0.02110 0.01271 -0.0708 0.7568 0.4708
-2.500 0.0995 0.02162 0.01435 -0.0724 0.7561 0.7692
-2.250 0.1107 0.02193 0.01452 -0.0686 0.7531 0.8158
-2.000 0.1079 0.02255 0.01507 -0.0629 0.7469 0.8436
-1.750 0.1279 0.02315 0.01557 -0.0607 0.7423 0.8672
-1.500 0.1520 0.02345 0.01573 -0.0592 0.7394 0.8887
-1.250 0.2146 0.02370 0.01579 -0.0648 0.7382 0.9081
-1.000 0.2983 0.02375 0.01563 -0.0749 0.7376 0.9262
-0.750 0.3613 0.02358 0.01529 -0.0815 0.7364 0.9387
-0.500 0.3965 0.02387 0.01553 -0.0837 0.7308 0.9496
-0.250 0.4239 0.02396 0.01556 -0.0841 0.7263 0.9574
0.000 0.4601 0.02376 0.01527 -0.0861 0.7234 0.9605
0.250 0.4956 0.02352 0.01493 -0.0878 0.7211 0.9634
0.500 0.5113 0.02394 0.01535 -0.0864 0.7143 0.9689
0.750 0.5380 0.02394 0.01531 -0.0868 0.7098 0.9721
1.000 0.5718 0.02372 0.01503 -0.0882 0.7070 0.9744
1.250 0.6058 0.02342 0.01467 -0.0895 0.7047 0.9764
1.500 0.6158 0.02407 0.01538 -0.0873 0.6959 0.9814
1.750 0.6451 0.02390 0.01518 -0.0879 0.6923 0.9836
2.000 0.6795 0.02358 0.01481 -0.0892 0.6899 0.9851
2.250 0.6939 0.02416 0.01545 -0.0879 0.6813 0.9891
2.500 0.7219 0.02400 0.01529 -0.0882 0.6773 0.9911
2.750 0.7548 0.02364 0.01492 -0.0891 0.6746 0.9926
3.000 0.7673 0.02426 0.01560 -0.0874 0.6657 0.9964
3.250 0.7966 0.02404 0.01539 -0.0879 0.6617 0.9980
3.500 0.8310 0.02362 0.01498 -0.0890 0.6590 0.9992
3.750 0.8249 0.02446 0.01589 -0.0838 0.6488 1.0000
4.000 0.8514 0.02412 0.01555 -0.0834 0.6452 1.0000
4.250 0.8426 0.02483 0.01632 -0.0775 0.6358 1.0000
4.500 0.8642 0.02461 0.01611 -0.0763 0.6311 1.0000
5.000 0.8723 0.02508 0.01667 -0.0683 0.6169 1.0000
5.250 0.9068 0.02451 0.01612 -0.0690 0.6136 1.0000
5.500 0.8686 0.02551 0.01715 -0.0582 0.6019 1.0000
5.750 0.9061 0.02491 0.01659 -0.0594 0.5986 1.0000
6.000 0.8674 0.02599 0.01768 -0.0489 0.5865 1.0000
6.250 0.9053 0.02526 0.01700 -0.0499 0.5832 1.0000
6.500 0.8745 0.02638 0.01814 -0.0412 0.5711 1.0000
7.000 0.8917 0.02664 0.01846 -0.0353 0.5554 1.0000
7.500 0.9205 0.02681 0.01873 -0.0312 0.5395 1.0000
7.750 0.9263 0.02746 0.01943 -0.0286 0.5293 1.0000
8.000 0.9585 0.02690 0.01892 -0.0287 0.5231 1.0000
8.250 0.9647 0.02768 0.01978 -0.0263 0.5118 1.0000
8.500 0.9905 0.02749 0.01964 -0.0259 0.5035 1.0000
8.750 1.0088 0.02773 0.01994 -0.0248 0.4932 1.0000
9.000 1.0212 0.02834 0.02062 -0.0232 0.4817 1.0000
9.250 1.0434 0.02843 0.02077 -0.0225 0.4715 1.0000
9.500 1.0668 0.02847 0.02085 -0.0220 0.4608 1.0000
9.750 1.0775 0.02925 0.02170 -0.0204 0.4481 1.0000
10.000 1.0912 0.02988 0.02238 -0.0191 0.4352 1.0000
10.250 1.1059 0.03046 0.02303 -0.0179 0.4220 1.0000
10.500 1.1203 0.03108 0.02368 -0.0167 0.4085 1.0000
10.750 1.1334 0.03179 0.02442 -0.0154 0.3946 1.0000
11.000 1.1412 0.03280 0.02545 -0.0137 0.3782 1.0000
11.250 1.1459 0.03402 0.02668 -0.0119 0.3599 1.0000
11.500 1.1496 0.03534 0.02796 -0.0101 0.3403 1.0000
11.750 1.1527 0.03677 0.02933 -0.0084 0.3208 1.0000
12.000 1.1537 0.03849 0.03107 -0.0068 0.3021 1.0000
12.250 1.1552 0.04027 0.03284 -0.0054 0.2832 1.0000
12.500 1.1559 0.04218 0.03472 -0.0040 0.2642 1.0000
13.000 1.1548 0.04655 0.03905 -0.0017 0.2250 1.0000
13.250 1.1522 0.04907 0.04154 -0.0007 0.2045 1.0000
13.500 1.1484 0.05183 0.04424 0.0002 0.1837 1.0000
13.750 1.1436 0.05484 0.04720 0.0009 0.1622 1.0000
14.000 1.1377 0.05808 0.05037 0.0014 0.1421 1.0000
14.250 1.1304 0.06162 0.05383 0.0017 0.1214 1.0000
14.500 1.1227 0.06534 0.05748 0.0018 0.1049 1.0000
14.750 1.1158 0.06911 0.06121 0.0017 0.0903 1.0000
15.000 1.1086 0.07305 0.06512 0.0015 0.0783 1.0000
15.250 1.1020 0.07704 0.06911 0.0010 0.0693 1.0000
15.500 1.0968 0.08096 0.07308 0.0005 0.0620 1.0000
15.750 1.0896 0.08522 0.07736 -0.0003 0.0569 1.0000
16.000 1.0863 0.08906 0.08131 -0.0010 0.0518 1.0000
16.250 1.0806 0.09328 0.08557 -0.0020 0.0487 1.0000
16.500 1.0784 0.09705 0.08943 -0.0029 0.0452 1.0000
16.750 1.0758 0.10094 0.09341 -0.0040 0.0421 1.0000
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Polar data table (+)
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