AH 95-160 (ah95160-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 200,000 Max Cl/Cd: 65.45 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah95160-il-200000.txt Download as CSV file: xf-ah95160-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 95-160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1367 0.10266 0.09827 -0.0750 0.7725 0.0604
-9.750 -0.1367 0.09910 0.09470 -0.0784 0.7707 0.0630
-9.500 -0.1630 0.09248 0.08817 -0.0913 0.7688 0.0644
-9.250 -0.1430 0.08967 0.08537 -0.0874 0.7667 0.0652
-9.000 -0.1271 0.08756 0.08326 -0.0864 0.7643 0.0661
-8.750 -0.1160 0.08507 0.08078 -0.0870 0.7617 0.0674
-8.500 -0.1089 0.08207 0.07778 -0.0889 0.7592 0.0691
-8.250 -0.1072 0.07808 0.07381 -0.0929 0.7570 0.0717
-8.000 -0.1537 0.06567 0.06111 -0.1167 0.7546 0.0746
-7.750 -0.1326 0.06301 0.05858 -0.1145 0.7529 0.0755
-7.500 -0.1599 0.04690 0.04151 -0.1235 0.7512 0.0561
-7.250 -0.1415 0.04426 0.03894 -0.1242 0.7487 0.0568
-7.000 -0.1221 0.04248 0.03714 -0.1248 0.7460 0.0577
-6.750 -0.1128 0.03527 0.02918 -0.1259 0.7435 0.0514
-6.500 -0.0947 0.03111 0.02437 -0.1261 0.7412 0.0509
-6.250 -0.0710 0.02920 0.02213 -0.1262 0.7391 0.0520
-6.000 -0.0459 0.02770 0.02024 -0.1263 0.7374 0.0543
-5.750 -0.0204 0.02622 0.01836 -0.1263 0.7357 0.0567
-5.500 0.0055 0.02555 0.01768 -0.1265 0.7337 0.0589
-5.250 0.0316 0.02490 0.01693 -0.1267 0.7307 0.0617
-5.000 0.0579 0.02414 0.01598 -0.1268 0.7278 0.0656
-4.750 0.0846 0.02374 0.01561 -0.1270 0.7254 0.0697
-4.500 0.1124 0.02342 0.01507 -0.1270 0.7234 0.0744
-4.250 0.1388 0.02271 0.01445 -0.1272 0.7215 0.0802
-4.000 0.1667 0.02235 0.01395 -0.1272 0.7198 0.0865
-3.750 0.1938 0.02190 0.01355 -0.1273 0.7182 0.0940
-3.500 0.2192 0.02170 0.01335 -0.1273 0.7155 0.1018
-3.250 0.2439 0.02174 0.01348 -0.1275 0.7122 0.1103
-3.000 0.2694 0.02157 0.01338 -0.1276 0.7095 0.1198
-2.750 0.2961 0.02146 0.01327 -0.1277 0.7072 0.1308
-2.500 0.3237 0.02128 0.01311 -0.1279 0.7052 0.1444
-2.250 0.3520 0.02096 0.01286 -0.1282 0.7034 0.1634
-2.000 0.3803 0.02057 0.01266 -0.1286 0.7018 0.2008
-1.750 0.4071 0.01951 0.01266 -0.1294 0.7003 0.4601
-1.500 0.4229 0.01988 0.01381 -0.1281 0.6960 0.6586
-1.250 0.4415 0.02035 0.01452 -0.1266 0.6924 0.7379
-1.000 0.4619 0.02060 0.01486 -0.1249 0.6897 0.7919
-0.750 0.4827 0.02071 0.01501 -0.1229 0.6876 0.8323
-0.500 0.5031 0.02079 0.01507 -0.1208 0.6860 0.8671
-0.250 0.5224 0.02087 0.01513 -0.1185 0.6846 0.8987
0.000 0.5423 0.02098 0.01519 -0.1162 0.6833 0.9304
0.250 0.5507 0.02281 0.01718 -0.1152 0.6752 0.9679
0.500 0.5895 0.02309 0.01738 -0.1180 0.6726 0.9998
0.750 0.6180 0.02333 0.01754 -0.1187 0.6707 0.9998
1.000 0.6489 0.02345 0.01756 -0.1196 0.6692 0.9998
1.250 0.6814 0.02347 0.01747 -0.1206 0.6681 0.9998
1.500 0.7138 0.02349 0.01740 -0.1214 0.6669 0.9998
1.750 0.7029 0.02689 0.02094 -0.1191 0.6558 0.9998
2.000 0.7328 0.02701 0.02100 -0.1197 0.6539 0.9998
2.250 0.7652 0.02693 0.02085 -0.1203 0.6527 0.9998
2.500 0.7984 0.02680 0.02066 -0.1211 0.6516 0.9998
2.750 0.8087 0.02858 0.02246 -0.1201 0.6463 0.9998
3.000 0.8571 0.02727 0.02105 -0.1220 0.6485 0.9998
3.250 0.7810 0.03554 0.02952 -0.1147 0.6251 0.9998
3.500 0.8068 0.03589 0.02985 -0.1147 0.6224 0.9998
3.750 0.8382 0.03576 0.02970 -0.1150 0.6209 0.9998
4.000 0.8727 0.03536 0.02928 -0.1155 0.6200 0.9998
4.250 0.8476 0.03975 0.03371 -0.1122 0.6070 0.9998
4.500 0.8788 0.03960 0.03354 -0.1125 0.6053 0.9998
4.750 0.9120 0.03925 0.03319 -0.1129 0.6042 0.9998
5.000 0.8962 0.04285 0.03682 -0.1102 0.5926 0.9998
5.250 0.9260 0.04273 0.03670 -0.1103 0.5904 0.9998
5.500 0.9597 0.04223 0.03621 -0.1106 0.5890 0.9998
5.750 0.9956 0.04151 0.03551 -0.1110 0.5881 0.9998
6.000 1.0331 0.04060 0.03462 -0.1115 0.5875 0.9998
6.250 1.0718 0.03952 0.03356 -0.1120 0.5871 0.9998
6.500 1.1125 0.03817 0.03225 -0.1126 0.5870 0.9998
6.750 1.1549 0.03657 0.03068 -0.1132 0.5869 0.9998
7.000 1.2017 0.03468 0.02883 -0.1144 0.5869 0.9998
7.250 1.2557 0.03237 0.02654 -0.1164 0.5869 0.9998
7.500 1.3168 0.02971 0.02390 -0.1195 0.5868 0.9998
7.750 1.3798 0.02686 0.02103 -0.1229 0.5861 0.9998
8.000 1.3473 0.02979 0.02410 -0.1160 0.5738 0.9998
8.250 1.4137 0.02690 0.02123 -0.1199 0.5730 0.9998
8.500 1.4701 0.02478 0.01910 -0.1230 0.5710 0.9998
8.750 1.4462 0.02688 0.02136 -0.1165 0.5604 0.9998
9.000 1.5034 0.02473 0.01922 -0.1197 0.5573 0.9998
9.250 1.4961 0.02594 0.02054 -0.1152 0.5484 0.9998
9.500 1.5366 0.02455 0.01919 -0.1163 0.5426 0.9998
9.750 1.5313 0.02586 0.02060 -0.1125 0.5326 0.9998
10.000 1.5773 0.02410 0.01882 -0.1139 0.5250 0.9998
10.250 1.5649 0.02603 0.02088 -0.1099 0.5123 0.9998
10.500 1.5658 0.02742 0.02233 -0.1074 0.4987 0.9998
10.750 1.5732 0.02844 0.02338 -0.1057 0.4836 0.9998
11.000 1.5822 0.02938 0.02431 -0.1040 0.4662 0.9998
11.250 1.5840 0.03098 0.02589 -0.1019 0.4458 0.9998
11.500 1.5847 0.03268 0.02752 -0.0997 0.4214 0.9998
11.750 1.5823 0.03464 0.02935 -0.0973 0.3934 0.9998
12.000 1.5750 0.03703 0.03156 -0.0946 0.3639 0.9998
12.250 1.5637 0.03987 0.03422 -0.0918 0.3352 0.9998
12.500 1.5507 0.04304 0.03720 -0.0892 0.3081 0.9998
12.750 1.5383 0.04637 0.04038 -0.0869 0.2823 0.9998
13.000 1.5267 0.04976 0.04363 -0.0849 0.2587 0.9998
13.250 1.5163 0.05318 0.04692 -0.0831 0.2366 0.9998
13.500 1.5065 0.05663 0.05024 -0.0814 0.2173 0.9998
13.750 1.4997 0.05989 0.05343 -0.0801 0.1992 0.9998
14.000 1.4941 0.06309 0.05655 -0.0788 0.1833 0.9998
14.250 1.4895 0.06624 0.05963 -0.0778 0.1695 0.9998
14.500 1.4853 0.06937 0.06268 -0.0767 0.1575 0.9998
14.750 1.4835 0.07230 0.06558 -0.0759 0.1464 0.9998
15.000 1.4834 0.07509 0.06838 -0.0751 0.1365 0.9998
15.250 1.4822 0.07799 0.07124 -0.0744 0.1282 0.9998
15.500 1.4823 0.08081 0.07406 -0.0738 0.1202 0.9998
15.750 1.4834 0.08348 0.07675 -0.0732 0.1131 0.9998
16.000 1.4836 0.08628 0.07951 -0.0726 0.1068 0.9998
16.250 1.4859 0.08886 0.08215 -0.0722 0.1007 0.9998
16.500 1.4870 0.09162 0.08491 -0.0718 0.0954 0.9998
16.750 1.4899 0.09406 0.08736 -0.0713 0.0904 0.9998
17.000 1.4921 0.09678 0.09017 -0.0712 0.0858 0.9998
17.250 1.4955 0.09895 0.09223 -0.0706 0.0815 0.9998
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