AH 93-157 (ah93157-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 93-157 (ah93157-il) Reynolds number: 500,000 Max Cl/Cd: 100.41 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93157-il-500000.txt Download as CSV file: xf-ah93157-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1284 0.10197 0.09899 -0.0890 0.8240 0.0296
-12.500 -0.3908 0.05331 0.04999 -0.1263 0.8428 0.0191
-12.250 -0.4233 0.04738 0.04388 -0.1289 0.8374 0.0190
-12.000 -0.4540 0.04305 0.03930 -0.1283 0.8325 0.0190
-11.750 -0.4791 0.03975 0.03580 -0.1257 0.8279 0.0190
-11.500 -0.5010 0.03688 0.03270 -0.1221 0.8234 0.0190
-11.250 -0.5189 0.03459 0.03014 -0.1177 0.8193 0.0191
-11.000 -0.5338 0.03263 0.02790 -0.1128 0.8155 0.0192
-10.750 -0.5402 0.03137 0.02641 -0.1084 0.8120 0.0193
-10.500 -0.5498 0.02812 0.02284 -0.1042 0.8084 0.0196
-10.250 -0.5425 0.02636 0.02089 -0.1019 0.8053 0.0198
-10.000 -0.5279 0.02551 0.01996 -0.1004 0.8028 0.0203
-9.750 -0.5126 0.02469 0.01901 -0.0989 0.8003 0.0208
-9.500 -0.4957 0.02393 0.01816 -0.0975 0.7977 0.0214
-9.250 -0.4792 0.02282 0.01688 -0.0960 0.7949 0.0220
-9.000 -0.4608 0.02193 0.01581 -0.0948 0.7921 0.0227
-8.750 -0.4408 0.02137 0.01507 -0.0937 0.7895 0.0234
-8.500 -0.4211 0.01978 0.01330 -0.0928 0.7872 0.0243
-8.250 -0.3990 0.01902 0.01247 -0.0922 0.7849 0.0249
-8.000 -0.3765 0.01850 0.01191 -0.0915 0.7825 0.0258
-7.750 -0.3538 0.01792 0.01126 -0.0908 0.7801 0.0267
-7.500 -0.3304 0.01736 0.01062 -0.0902 0.7776 0.0277
-7.250 -0.3063 0.01704 0.01020 -0.0897 0.7750 0.0287
-7.000 -0.2842 0.01602 0.00915 -0.0890 0.7726 0.0302
-6.750 -0.2602 0.01563 0.00873 -0.0885 0.7704 0.0317
-6.500 -0.2359 0.01526 0.00829 -0.0881 0.7682 0.0332
-6.250 -0.2117 0.01496 0.00794 -0.0875 0.7659 0.0346
-6.000 -0.1907 0.01428 0.00727 -0.0865 0.7632 0.0368
-5.750 -0.1665 0.01400 0.00699 -0.0860 0.7605 0.0394
-5.500 -0.1415 0.01375 0.00669 -0.0856 0.7581 0.0418
-5.250 -0.1191 0.01323 0.00616 -0.0848 0.7557 0.0453
-5.000 -0.0936 0.01301 0.00590 -0.0845 0.7535 0.0492
-4.750 -0.0697 0.01271 0.00559 -0.0839 0.7513 0.0545
-4.500 -0.0453 0.01250 0.00539 -0.0834 0.7487 0.0602
-4.250 -0.0217 0.01218 0.00512 -0.0828 0.7458 0.0686
-4.000 0.0029 0.01192 0.00490 -0.0823 0.7432 0.0799
-3.750 0.0278 0.01165 0.00468 -0.0819 0.7407 0.0967
-3.500 0.0526 0.01136 0.00448 -0.0816 0.7384 0.1241
-3.250 0.0770 0.01107 0.00433 -0.0812 0.7361 0.1683
-3.000 0.0986 0.01068 0.00422 -0.0803 0.7334 0.2360
-2.750 0.1188 0.01019 0.00410 -0.0793 0.7301 0.3314
-2.500 0.1368 0.00955 0.00394 -0.0778 0.7271 0.4610
-2.250 0.1481 0.00859 0.00377 -0.0748 0.7244 0.6672
-2.000 0.1687 0.00867 0.00428 -0.0725 0.7221 0.7984
-1.750 0.1955 0.00895 0.00450 -0.0720 0.7196 0.8275
-1.500 0.2203 0.00920 0.00473 -0.0711 0.7164 0.8435
-1.250 0.2462 0.00952 0.00504 -0.0702 0.7133 0.8526
-1.000 0.2725 0.00971 0.00518 -0.0697 0.7102 0.8616
-0.750 0.2993 0.00995 0.00537 -0.0690 0.7075 0.8685
-0.500 0.3259 0.01016 0.00551 -0.0684 0.7049 0.8767
-0.250 0.3499 0.01036 0.00572 -0.0672 0.7015 0.8825
0.000 0.3735 0.01047 0.00582 -0.0662 0.6977 0.8906
0.250 0.3992 0.01065 0.00599 -0.0650 0.6944 0.8981
0.500 0.4255 0.01078 0.00608 -0.0640 0.6915 0.9076
0.750 0.4510 0.01095 0.00621 -0.0632 0.6883 0.9171
1.000 0.4831 0.01093 0.00621 -0.0637 0.6841 0.9220
1.250 0.5127 0.01089 0.00615 -0.0641 0.6802 0.9256
1.500 0.5339 0.01080 0.00602 -0.0629 0.6766 0.9293
1.750 0.5554 0.01072 0.00589 -0.0619 0.6731 0.9323
2.000 0.5816 0.01060 0.00581 -0.0617 0.6683 0.9338
2.250 0.6097 0.01051 0.00570 -0.0620 0.6637 0.9354
2.500 0.6378 0.01044 0.00558 -0.0622 0.6598 0.9369
2.750 0.6603 0.01038 0.00553 -0.0614 0.6550 0.9390
3.000 0.6805 0.01030 0.00546 -0.0601 0.6498 0.9418
3.250 0.7009 0.01022 0.00536 -0.0588 0.6453 0.9441
3.500 0.7233 0.01014 0.00528 -0.0579 0.6398 0.9458
3.750 0.7485 0.01006 0.00522 -0.0576 0.6340 0.9473
4.000 0.7753 0.01001 0.00514 -0.0577 0.6290 0.9485
4.250 0.7974 0.00997 0.00514 -0.0568 0.6223 0.9502
4.500 0.8209 0.00993 0.00509 -0.0561 0.6159 0.9521
4.750 0.8424 0.00991 0.00509 -0.0551 0.6094 0.9538
5.000 0.8622 0.00987 0.00506 -0.0538 0.6021 0.9556
5.250 0.8826 0.00987 0.00506 -0.0526 0.5952 0.9573
5.500 0.9038 0.00985 0.00506 -0.0516 0.5872 0.9589
5.750 0.9267 0.00987 0.00508 -0.0509 0.5793 0.9602
6.000 0.9483 0.00990 0.00512 -0.0500 0.5704 0.9616
6.250 0.9688 0.00995 0.00518 -0.0489 0.5609 0.9632
6.500 0.9887 0.01003 0.00525 -0.0477 0.5516 0.9652
6.750 1.0057 0.01010 0.00534 -0.0459 0.5409 0.9672
7.000 1.0206 0.01018 0.00543 -0.0437 0.5310 0.9693
7.250 1.0362 0.01032 0.00555 -0.0418 0.5205 0.9712
7.500 1.0549 0.01053 0.00577 -0.0406 0.5076 0.9732
7.750 1.0745 0.01081 0.00605 -0.0397 0.4939 0.9755
8.000 1.0944 0.01112 0.00637 -0.0389 0.4808 0.9776
8.250 1.1132 0.01151 0.00676 -0.0381 0.4658 0.9797
8.500 1.1303 0.01205 0.00725 -0.0373 0.4475 0.9821
8.750 1.1479 0.01278 0.00792 -0.0369 0.4242 0.9847
9.000 1.1646 0.01364 0.00871 -0.0366 0.4005 0.9880
9.250 1.1817 0.01448 0.00950 -0.0364 0.3804 0.9935
9.500 1.1897 0.01536 0.01034 -0.0344 0.3626 1.0000
9.750 1.1935 0.01620 0.01114 -0.0315 0.3468 1.0000
10.000 1.1983 0.01718 0.01207 -0.0291 0.3286 1.0000
10.250 1.2031 0.01829 0.01310 -0.0268 0.3095 1.0000
10.500 1.2091 0.01943 0.01419 -0.0249 0.2919 1.0000
10.750 1.2152 0.02063 0.01533 -0.0230 0.2729 1.0000
11.000 1.2212 0.02188 0.01651 -0.0213 0.2534 1.0000
11.250 1.2251 0.02330 0.01785 -0.0194 0.2324 1.0000
11.500 1.2286 0.02480 0.01925 -0.0177 0.2107 1.0000
11.750 1.2310 0.02644 0.02079 -0.0159 0.1884 1.0000
12.000 1.2327 0.02818 0.02242 -0.0142 0.1648 1.0000
12.250 1.2323 0.03013 0.02424 -0.0125 0.1396 1.0000
12.500 1.2309 0.03225 0.02622 -0.0108 0.1152 1.0000
12.750 1.2283 0.03453 0.02836 -0.0092 0.0916 1.0000
13.000 1.2259 0.03689 0.03059 -0.0077 0.0697 1.0000
13.250 1.2248 0.03923 0.03284 -0.0065 0.0538 1.0000
13.500 1.2255 0.04149 0.03506 -0.0055 0.0436 1.0000
13.750 1.2268 0.04379 0.03734 -0.0046 0.0366 1.0000
14.000 1.2273 0.04623 0.03979 -0.0038 0.0320 1.0000
14.250 1.2311 0.04840 0.04202 -0.0032 0.0286 1.0000
14.500 1.2308 0.05104 0.04469 -0.0026 0.0259 1.0000
14.750 1.2356 0.05325 0.04697 -0.0023 0.0238 1.0000
15.000 1.2365 0.05589 0.04966 -0.0020 0.0224 1.0000
15.250 1.2332 0.05904 0.05288 -0.0017 0.0211 1.0000
15.500 1.2367 0.06154 0.05547 -0.0016 0.0199 1.0000
15.750 1.2401 0.06408 0.05806 -0.0017 0.0186 1.0000
16.000 1.2381 0.06730 0.06134 -0.0017 0.0179 1.0000
16.250 1.2308 0.07119 0.06530 -0.0019 0.0171 1.0000
16.500 1.2336 0.07395 0.06817 -0.0022 0.0165 1.0000
16.750 1.2333 0.07716 0.07147 -0.0026 0.0159 1.0000
17.000 1.2336 0.08034 0.07473 -0.0031 0.0153 1.0000
17.250 1.2320 0.08380 0.07826 -0.0037 0.0149 1.0000
17.500 1.2301 0.08734 0.08187 -0.0044 0.0144 1.0000
17.750 1.2243 0.09141 0.08600 -0.0053 0.0140 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 93-157 (ah93157-il)