AH 94-145 (ah94145-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 94-145 (ah94145-il) Reynolds number: 500,000 Max Cl/Cd: 135.6 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah94145-il-500000.txt Download as CSV file: xf-ah94145-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-145
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1933 0.10422 0.10069 -0.0601 0.7192 0.0267
-10.000 -0.2061 0.09630 0.09281 -0.0681 0.7178 0.0280
-9.750 -0.2006 0.09290 0.08940 -0.0684 0.7159 0.0283
-9.500 -0.1907 0.09063 0.08712 -0.0689 0.7141 0.0285
-9.250 -0.1810 0.08828 0.08475 -0.0697 0.7123 0.0289
-9.000 -0.1728 0.08560 0.08205 -0.0711 0.7103 0.0293
-8.750 -0.1658 0.08247 0.07894 -0.0731 0.7089 0.0299
-8.500 -0.1608 0.07880 0.07530 -0.0759 0.7072 0.0308
-8.250 -0.1784 0.06536 0.06192 -0.0948 0.7055 0.0329
-8.000 -0.2561 0.02698 0.02195 -0.1199 0.7048 0.0221
-7.750 -0.2356 0.02353 0.01793 -0.1209 0.7028 0.0228
-7.500 -0.2107 0.02161 0.01558 -0.1215 0.7007 0.0234
-7.250 -0.1851 0.01983 0.01344 -0.1220 0.6988 0.0238
-7.000 -0.1588 0.01846 0.01193 -0.1224 0.6971 0.0244
-6.750 -0.1311 0.01778 0.01115 -0.1228 0.6954 0.0251
-6.500 -0.1032 0.01717 0.01042 -0.1232 0.6935 0.0259
-6.250 -0.0748 0.01646 0.00961 -0.1236 0.6918 0.0268
-6.000 -0.0461 0.01590 0.00892 -0.1239 0.6899 0.0277
-5.750 -0.0181 0.01508 0.00806 -0.1243 0.6880 0.0291
-5.500 0.0107 0.01473 0.00771 -0.1248 0.6861 0.0306
-5.250 0.0397 0.01434 0.00723 -0.1251 0.6844 0.0322
-5.000 0.0685 0.01376 0.00659 -0.1255 0.6827 0.0339
-4.750 0.0976 0.01345 0.00627 -0.1260 0.6810 0.0361
-4.500 0.1270 0.01326 0.00600 -0.1264 0.6792 0.0386
-4.250 0.1561 0.01299 0.00573 -0.1269 0.6773 0.0424
-4.000 0.1856 0.01271 0.00545 -0.1274 0.6758 0.0466
-3.750 0.2151 0.01251 0.00528 -0.1279 0.6742 0.0517
-3.500 0.2447 0.01228 0.00509 -0.1284 0.6724 0.0582
-3.250 0.2743 0.01211 0.00492 -0.1289 0.6706 0.0654
-3.000 0.3039 0.01201 0.00482 -0.1294 0.6687 0.0729
-2.750 0.3337 0.01181 0.00464 -0.1300 0.6669 0.0817
-2.500 0.3635 0.01167 0.00448 -0.1305 0.6652 0.0905
-2.250 0.3933 0.01158 0.00438 -0.1310 0.6636 0.1004
-2.000 0.4232 0.01149 0.00431 -0.1317 0.6620 0.1144
-1.750 0.4531 0.01136 0.00427 -0.1323 0.6602 0.1373
-1.500 0.4833 0.01102 0.00422 -0.1332 0.6584 0.2111
-1.250 0.5144 0.01038 0.00422 -0.1347 0.6565 0.4096
-1.000 0.5454 0.00986 0.00431 -0.1359 0.6547 0.6098
-0.750 0.5745 0.00966 0.00440 -0.1362 0.6529 0.7093
-0.500 0.6016 0.00957 0.00450 -0.1359 0.6512 0.7770
-0.250 0.6277 0.00958 0.00458 -0.1353 0.6495 0.8254
0.000 0.6543 0.00964 0.00464 -0.1349 0.6478 0.8557
0.250 0.6797 0.00975 0.00474 -0.1342 0.6461 0.8788
0.500 0.7049 0.00988 0.00487 -0.1336 0.6443 0.8975
0.750 0.7289 0.00992 0.00496 -0.1327 0.6425 0.9146
1.000 0.7473 0.00993 0.00501 -0.1304 0.6405 0.9370
1.250 0.7597 0.00982 0.00494 -0.1267 0.6384 0.9659
1.500 0.7908 0.00969 0.00481 -0.1272 0.6363 0.9998
1.750 0.8220 0.00977 0.00484 -0.1282 0.6345 0.9998
2.000 0.8534 0.00985 0.00488 -0.1293 0.6327 0.9998
2.250 0.8849 0.00996 0.00494 -0.1303 0.6310 0.9998
2.500 0.9160 0.01014 0.00509 -0.1312 0.6290 0.9998
2.750 0.9462 0.01023 0.00522 -0.1321 0.6269 0.9998
3.000 0.9765 0.01033 0.00534 -0.1329 0.6246 0.9998
3.250 1.0069 0.01043 0.00545 -0.1337 0.6222 0.9998
3.500 1.0375 0.01051 0.00553 -0.1346 0.6200 0.9998
3.750 1.0681 0.01057 0.00558 -0.1354 0.6179 0.9998
4.000 1.0989 0.01065 0.00563 -0.1362 0.6159 0.9998
4.250 1.1292 0.01081 0.00577 -0.1369 0.6136 0.9998
4.500 1.1579 0.01088 0.00592 -0.1374 0.6105 0.9998
4.750 1.1870 0.01091 0.00599 -0.1380 0.6069 0.9998
5.000 1.2169 0.01085 0.00593 -0.1385 0.6030 0.9998
5.250 1.2472 0.01081 0.00583 -0.1391 0.5990 0.9998
5.500 1.2747 0.01079 0.00590 -0.1393 0.5935 0.9998
5.750 1.3035 0.01071 0.00583 -0.1397 0.5878 0.9998
6.000 1.3326 0.01071 0.00579 -0.1401 0.5830 0.9998
6.250 1.3595 0.01073 0.00592 -0.1402 0.5768 0.9998
6.500 1.3875 0.01074 0.00594 -0.1405 0.5712 0.9998
6.750 1.4151 0.01082 0.00606 -0.1407 0.5659 0.9998
7.000 1.4420 0.01089 0.00621 -0.1408 0.5593 0.9998
7.250 1.4690 0.01097 0.00628 -0.1409 0.5526 0.9998
7.500 1.4947 0.01107 0.00646 -0.1408 0.5430 0.9998
7.750 1.5201 0.01121 0.00664 -0.1407 0.5328 0.9998
8.000 1.5446 0.01140 0.00683 -0.1404 0.5215 0.9998
8.250 1.5678 0.01165 0.00709 -0.1399 0.5076 0.9998
8.500 1.5891 0.01198 0.00742 -0.1391 0.4893 0.9998
8.750 1.6059 0.01252 0.00787 -0.1376 0.4646 0.9998
9.000 1.6166 0.01333 0.00856 -0.1352 0.4314 0.9998
9.250 1.6151 0.01455 0.00959 -0.1308 0.3933 0.9998
9.500 1.6065 0.01635 0.01120 -0.1262 0.3568 0.9998
9.750 1.5969 0.01864 0.01333 -0.1223 0.3219 0.9998
10.000 1.5875 0.02131 0.01586 -0.1191 0.2905 0.9998
10.250 1.5792 0.02412 0.01854 -0.1165 0.2625 0.9998
10.500 1.5710 0.02699 0.02130 -0.1139 0.2370 0.9998
10.750 1.5652 0.02970 0.02390 -0.1116 0.2136 0.9998
11.000 1.5590 0.03244 0.02655 -0.1093 0.1930 0.9998
11.250 1.5551 0.03499 0.02903 -0.1073 0.1745 0.9998
11.500 1.5521 0.03748 0.03145 -0.1053 0.1577 0.9998
11.750 1.5504 0.03993 0.03385 -0.1035 0.1430 0.9998
12.000 1.5500 0.04231 0.03619 -0.1019 0.1298 0.9998
12.250 1.5503 0.04469 0.03852 -0.1005 0.1179 0.9998
12.500 1.5508 0.04711 0.04091 -0.0991 0.1073 0.9998
12.750 1.5524 0.04945 0.04321 -0.0978 0.0979 0.9998
13.000 1.5557 0.05167 0.04544 -0.0967 0.0899 0.9998
13.250 1.5578 0.05404 0.04780 -0.0956 0.0827 0.9998
13.500 1.5608 0.05637 0.05014 -0.0946 0.0762 0.9998
13.750 1.5639 0.05869 0.05248 -0.0936 0.0706 0.9998
14.000 1.5664 0.06110 0.05489 -0.0927 0.0655 0.9998
14.250 1.5689 0.06356 0.05739 -0.0918 0.0611 0.9998
14.500 1.5728 0.06589 0.05975 -0.0911 0.0572 0.9998
14.750 1.5712 0.06887 0.06273 -0.0902 0.0535 0.9998
15.000 1.5777 0.07095 0.06489 -0.0896 0.0507 0.9998
15.250 1.5794 0.07360 0.06757 -0.0890 0.0479 0.9998
15.500 1.5774 0.07671 0.07070 -0.0883 0.0451 0.9998
15.750 1.5826 0.07903 0.07311 -0.0878 0.0431 0.9998
16.000 1.5851 0.08167 0.07580 -0.0874 0.0410 0.9998
16.250 1.5832 0.08486 0.07902 -0.0869 0.0390 0.9998
16.500 1.5831 0.08785 0.08209 -0.0866 0.0374 0.9998
16.750 1.5864 0.09048 0.08480 -0.0863 0.0359 0.9998
17.000 1.5878 0.09335 0.08773 -0.0862 0.0344 0.9998
17.250 1.5856 0.09671 0.09113 -0.0860 0.0330 0.9998
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