AH 95-160 (ah95160-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 95-160 (ah95160-il) Reynolds number: 500,000 Max Cl/Cd: 130.27 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah95160-il-500000.txt Download as CSV file: xf-ah95160-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2011 0.09845 0.09487 -0.0693 0.7103 0.0320
-10.250 -0.3986 0.04434 0.04057 -0.1096 0.7118 0.0228
-10.000 -0.4396 0.03355 0.02898 -0.1156 0.7099 0.0225
-9.750 -0.4357 0.02910 0.02395 -0.1165 0.7080 0.0228
-9.500 -0.4193 0.02679 0.02119 -0.1168 0.7061 0.0232
-9.250 -0.4013 0.02443 0.01853 -0.1171 0.7043 0.0237
-9.000 -0.3775 0.02344 0.01746 -0.1173 0.7025 0.0242
-8.750 -0.3530 0.02256 0.01643 -0.1175 0.7005 0.0247
-8.500 -0.3279 0.02158 0.01532 -0.1177 0.6989 0.0252
-8.250 -0.3024 0.02057 0.01416 -0.1180 0.6971 0.0258
-8.000 -0.2764 0.01963 0.01304 -0.1181 0.6952 0.0265
-7.750 -0.2497 0.01887 0.01210 -0.1183 0.6933 0.0271
-7.500 -0.2239 0.01778 0.01091 -0.1185 0.6915 0.0279
-7.250 -0.1966 0.01723 0.01034 -0.1188 0.6898 0.0288
-7.000 -0.1688 0.01682 0.00986 -0.1190 0.6881 0.0299
-6.750 -0.1408 0.01640 0.00933 -0.1193 0.6864 0.0311
-6.500 -0.1136 0.01576 0.00859 -0.1195 0.6846 0.0324
-6.250 -0.0858 0.01543 0.00826 -0.1197 0.6827 0.0337
-6.000 -0.0573 0.01506 0.00786 -0.1200 0.6813 0.0354
-5.750 -0.0292 0.01459 0.00734 -0.1203 0.6798 0.0372
-5.500 -0.0007 0.01427 0.00705 -0.1207 0.6781 0.0394
-5.250 0.0283 0.01409 0.00681 -0.1210 0.6763 0.0421
-5.000 0.0567 0.01371 0.00647 -0.1214 0.6744 0.0453
-4.750 0.0857 0.01352 0.00622 -0.1217 0.6726 0.0488
-4.500 0.1145 0.01324 0.00597 -0.1221 0.6710 0.0531
-4.250 0.1436 0.01303 0.00573 -0.1225 0.6695 0.0579
-4.000 0.1728 0.01296 0.00564 -0.1229 0.6680 0.0630
-3.750 0.2017 0.01283 0.00551 -0.1233 0.6663 0.0686
-3.500 0.2310 0.01278 0.00545 -0.1237 0.6648 0.0741
-3.250 0.2600 0.01252 0.00525 -0.1242 0.6631 0.0810
-3.000 0.2893 0.01239 0.00512 -0.1246 0.6613 0.0874
-2.750 0.3185 0.01222 0.00499 -0.1251 0.6595 0.0956
-2.500 0.3479 0.01206 0.00485 -0.1256 0.6578 0.1048
-2.250 0.3773 0.01194 0.00475 -0.1261 0.6562 0.1156
-2.000 0.4068 0.01177 0.00463 -0.1266 0.6546 0.1338
-1.750 0.4364 0.01152 0.00453 -0.1272 0.6530 0.1789
-1.500 0.4657 0.01102 0.00447 -0.1281 0.6514 0.3156
-1.250 0.4947 0.01054 0.00455 -0.1290 0.6496 0.5040
-1.000 0.5232 0.01029 0.00468 -0.1294 0.6482 0.6232
-0.750 0.5516 0.01019 0.00477 -0.1296 0.6465 0.6852
-0.500 0.5799 0.01015 0.00486 -0.1297 0.6446 0.7283
-0.250 0.6079 0.01014 0.00493 -0.1297 0.6427 0.7640
0.000 0.6360 0.01015 0.00499 -0.1298 0.6408 0.7928
0.250 0.6637 0.01016 0.00504 -0.1297 0.6391 0.8183
0.500 0.6915 0.01019 0.00509 -0.1296 0.6375 0.8403
0.750 0.7188 0.01024 0.00514 -0.1294 0.6360 0.8617
1.000 0.7427 0.01029 0.00523 -0.1284 0.6344 0.8907
1.250 0.7629 0.01039 0.00537 -0.1264 0.6326 0.9207
1.500 0.7817 0.01036 0.00541 -0.1243 0.6307 0.9473
1.750 0.8064 0.01034 0.00543 -0.1236 0.6287 0.9715
2.000 0.8430 0.01036 0.00545 -0.1256 0.6267 0.9912
2.250 0.8759 0.01042 0.00549 -0.1271 0.6247 0.9998
2.500 0.9068 0.01048 0.00553 -0.1280 0.6227 0.9998
2.750 0.9377 0.01056 0.00556 -0.1290 0.6210 0.9998
3.000 0.9687 0.01064 0.00561 -0.1299 0.6193 0.9998
3.250 0.9994 0.01081 0.00572 -0.1307 0.6174 0.9998
3.500 1.0284 0.01095 0.00590 -0.1313 0.6154 0.9998
3.750 1.0572 0.01106 0.00605 -0.1319 0.6130 0.9998
4.000 1.0862 0.01116 0.00617 -0.1324 0.6105 0.9998
4.250 1.1156 0.01123 0.00625 -0.1330 0.6082 0.9998
4.500 1.1454 0.01126 0.00628 -0.1336 0.6059 0.9998
4.750 1.1755 0.01130 0.00628 -0.1342 0.6036 0.9998
5.000 1.2052 0.01141 0.00637 -0.1348 0.6010 0.9998
5.250 1.2320 0.01145 0.00650 -0.1350 0.5972 0.9998
5.500 1.2601 0.01142 0.00650 -0.1352 0.5931 0.9998
5.750 1.2895 0.01133 0.00638 -0.1357 0.5890 0.9998
6.000 1.3181 0.01131 0.00634 -0.1360 0.5846 0.9998
6.250 1.3442 0.01129 0.00640 -0.1359 0.5788 0.9998
6.500 1.3720 0.01123 0.00635 -0.1361 0.5736 0.9998
6.750 1.3996 0.01129 0.00640 -0.1363 0.5689 0.9998
7.000 1.4252 0.01136 0.00656 -0.1362 0.5632 0.9998
7.250 1.4519 0.01140 0.00662 -0.1362 0.5579 0.9998
7.500 1.4779 0.01151 0.00676 -0.1362 0.5524 0.9998
7.750 1.5028 0.01162 0.00694 -0.1360 0.5455 0.9998
8.000 1.5280 0.01174 0.00706 -0.1358 0.5389 0.9998
8.250 1.5515 0.01191 0.00730 -0.1354 0.5301 0.9998
8.500 1.5743 0.01211 0.00752 -0.1348 0.5206 0.9998
8.750 1.5951 0.01236 0.00777 -0.1339 0.5090 0.9998
9.000 1.6138 0.01270 0.00812 -0.1327 0.4953 0.9998
9.250 1.6292 0.01316 0.00856 -0.1309 0.4793 0.9998
9.500 1.6384 0.01376 0.00913 -0.1281 0.4601 0.9998
9.750 1.6413 0.01474 0.01005 -0.1247 0.4368 0.9998
10.000 1.6382 0.01624 0.01145 -0.1210 0.4092 0.9998
10.250 1.6289 0.01845 0.01352 -0.1172 0.3793 0.9998
10.500 1.6163 0.02124 0.01618 -0.1137 0.3497 0.9998
10.750 1.6026 0.02435 0.01916 -0.1105 0.3224 0.9998
11.000 1.5896 0.02748 0.02218 -0.1075 0.2965 0.9998
11.250 1.5779 0.03055 0.02514 -0.1047 0.2732 0.9998
11.500 1.5675 0.03354 0.02804 -0.1021 0.2514 0.9998
11.750 1.5580 0.03650 0.03092 -0.0996 0.2315 0.9998
12.000 1.5523 0.03925 0.03359 -0.0976 0.2123 0.9998
12.250 1.5478 0.04197 0.03623 -0.0957 0.1946 0.9998
12.500 1.5442 0.04467 0.03886 -0.0940 0.1786 0.9998
12.750 1.5426 0.04723 0.04137 -0.0925 0.1640 0.9998
13.000 1.5417 0.04979 0.04388 -0.0911 0.1510 0.9998
13.250 1.5418 0.05227 0.04632 -0.0898 0.1393 0.9998
13.500 1.5417 0.05482 0.04884 -0.0886 0.1287 0.9998
13.750 1.5430 0.05727 0.05125 -0.0876 0.1191 0.9998
14.000 1.5458 0.05961 0.05360 -0.0866 0.1109 0.9998
14.250 1.5473 0.06208 0.05605 -0.0856 0.1035 0.9998
14.500 1.5497 0.06450 0.05847 -0.0848 0.0967 0.9998
14.750 1.5522 0.06694 0.06093 -0.0840 0.0907 0.9998
15.000 1.5548 0.06939 0.06339 -0.0832 0.0849 0.9998
15.250 1.5568 0.07195 0.06596 -0.0825 0.0799 0.9998
15.500 1.5601 0.07434 0.06838 -0.0819 0.0751 0.9998
15.750 1.5598 0.07720 0.07125 -0.0813 0.0708 0.9998
16.000 1.5645 0.07950 0.07360 -0.0808 0.0669 0.9998
16.250 1.5637 0.08248 0.07658 -0.0803 0.0632 0.9998
16.500 1.5668 0.08501 0.07918 -0.0799 0.0600 0.9998
16.750 1.5688 0.08768 0.08189 -0.0795 0.0569 0.9998
17.000 1.5661 0.09095 0.08516 -0.0792 0.0541 0.9998
17.250 1.5698 0.09346 0.08775 -0.0790 0.0517 0.9998
17.500 1.5712 0.09629 0.09064 -0.0788 0.0493 0.9998
17.750 1.5696 0.09952 0.09389 -0.0787 0.0472 0.9998
18.000 1.5689 0.10267 0.09710 -0.0787 0.0453 0.9998
18.250 1.5718 0.10533 0.09984 -0.0788 0.0435 0.9998
18.500 1.5712 0.10848 0.10304 -0.0789 0.0419 0.9998
18.750 1.5677 0.11203 0.10662 -0.0792 0.0402 0.9998
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