FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-K-170/22 (fx73k170-il) Reynolds number: 500,000 Max Cl/Cd: 112.89 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73k170-il-500000.txt Download as CSV file: xf-fx73k170-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-K-170/22
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 -0.0315 0.04051 0.03719 -0.1563 0.7989 0.0290
-10.250 -0.0605 0.03483 0.03144 -0.1592 0.7969 0.0289
-10.000 -0.0850 0.03076 0.02728 -0.1605 0.7943 0.0289
-9.750 -0.1057 0.02763 0.02405 -0.1607 0.7915 0.0289
-9.500 -0.1300 0.02552 0.02177 -0.1595 0.7886 0.0296
-9.250 -0.1538 0.02570 0.02173 -0.1552 0.7858 0.0304
-9.000 -0.2459 0.02583 0.02015 -0.1544 0.7870 0.0155
-8.750 -0.2272 0.02537 0.01951 -0.1534 0.7851 0.0153
-8.500 -0.2098 0.02373 0.01770 -0.1525 0.7831 0.0151
-8.250 -0.1949 0.02226 0.01605 -0.1509 0.7809 0.0153
-8.000 -0.1768 0.02044 0.01409 -0.1498 0.7785 0.0154
-7.750 -0.1565 0.01941 0.01297 -0.1489 0.7761 0.0155
-7.500 -0.1370 0.01827 0.01181 -0.1480 0.7738 0.0162
-7.250 -0.1159 0.01753 0.01099 -0.1472 0.7718 0.0165
-7.000 -0.0937 0.01696 0.01036 -0.1466 0.7699 0.0170
-6.750 -0.0720 0.01646 0.00980 -0.1460 0.7680 0.0177
-6.500 -0.0522 0.01603 0.00936 -0.1449 0.7656 0.0186
-6.250 -0.0316 0.01559 0.00888 -0.1439 0.7630 0.0192
-6.000 -0.0145 0.01476 0.00801 -0.1424 0.7604 0.0203
-5.750 0.0074 0.01426 0.00748 -0.1418 0.7581 0.0215
-5.500 0.0313 0.01384 0.00700 -0.1414 0.7561 0.0228
-5.250 0.0550 0.01336 0.00646 -0.1410 0.7542 0.0263
-5.000 0.0791 0.01308 0.00614 -0.1406 0.7522 0.0306
-4.750 0.0990 0.01256 0.00572 -0.1395 0.7495 0.0486
-4.500 0.1194 0.01198 0.00538 -0.1386 0.7468 0.0998
-4.250 0.1393 0.01125 0.00502 -0.1378 0.7442 0.1946
-4.000 0.1589 0.01046 0.00466 -0.1370 0.7420 0.3211
-3.750 0.1785 0.00977 0.00443 -0.1360 0.7401 0.4599
-3.500 0.2040 0.00967 0.00449 -0.1357 0.7382 0.5328
-3.250 0.2283 0.00976 0.00462 -0.1350 0.7357 0.5648
-3.000 0.2536 0.00984 0.00467 -0.1345 0.7329 0.5808
-2.750 0.2803 0.00990 0.00471 -0.1343 0.7303 0.5920
-2.500 0.3080 0.00998 0.00472 -0.1342 0.7280 0.6034
-2.250 0.3363 0.01010 0.00477 -0.1343 0.7261 0.6152
-2.000 0.3655 0.01021 0.00486 -0.1345 0.7242 0.6244
-1.750 0.3923 0.01032 0.00490 -0.1344 0.7218 0.6317
-1.500 0.4169 0.01033 0.00496 -0.1338 0.7188 0.6364
-1.250 0.4434 0.01037 0.00499 -0.1336 0.7160 0.6416
-1.000 0.4709 0.01039 0.00493 -0.1337 0.7135 0.6466
-0.750 0.4994 0.01036 0.00488 -0.1339 0.7114 0.6505
-0.500 0.5288 0.01037 0.00485 -0.1344 0.7095 0.6540
-0.250 0.5558 0.01042 0.00487 -0.1344 0.7071 0.6577
0.000 0.5797 0.01045 0.00491 -0.1337 0.7040 0.6616
0.250 0.6057 0.01045 0.00489 -0.1336 0.7012 0.6646
0.500 0.6332 0.01041 0.00485 -0.1336 0.6986 0.6674
0.750 0.6619 0.01039 0.00481 -0.1340 0.6963 0.6702
1.000 0.6913 0.01040 0.00478 -0.1345 0.6943 0.6733
1.250 0.7157 0.01045 0.00484 -0.1340 0.6914 0.6764
1.500 0.7399 0.01049 0.00488 -0.1335 0.6882 0.6792
1.750 0.7661 0.01045 0.00486 -0.1333 0.6851 0.6815
2.000 0.7941 0.01042 0.00483 -0.1335 0.6824 0.6839
2.250 0.8232 0.01041 0.00480 -0.1340 0.6800 0.6864
2.500 0.8479 0.01047 0.00489 -0.1336 0.6770 0.6893
2.750 0.8711 0.01051 0.00496 -0.1328 0.6734 0.6919
3.000 0.8970 0.01052 0.00496 -0.1327 0.6700 0.6945
3.250 0.9247 0.01049 0.00494 -0.1328 0.6671 0.6970
3.500 0.9546 0.01052 0.00495 -0.1335 0.6643 0.6994
3.750 0.9745 0.01057 0.00510 -0.1321 0.6604 0.7018
4.000 0.9983 0.01060 0.00516 -0.1315 0.6566 0.7045
4.250 1.0248 0.01062 0.00518 -0.1314 0.6531 0.7074
4.500 1.0547 0.01068 0.00521 -0.1321 0.6498 0.7103
4.750 1.0732 0.01073 0.00535 -0.1305 0.6455 0.7128
5.000 1.0959 0.01075 0.00543 -0.1296 0.6410 0.7154
5.250 1.1220 0.01079 0.00549 -0.1295 0.6373 0.7183
5.500 1.1471 0.01087 0.00559 -0.1292 0.6331 0.7213
5.750 1.1646 0.01093 0.00573 -0.1273 0.6276 0.7248
6.000 1.1882 0.01096 0.00576 -0.1267 0.6225 0.7277
6.250 1.2091 0.01102 0.00589 -0.1255 0.6169 0.7306
6.500 1.2252 0.01108 0.00602 -0.1233 0.6105 0.7338
6.750 1.2505 0.01115 0.00608 -0.1231 0.6047 0.7375
7.000 1.2568 0.01124 0.00626 -0.1189 0.5973 0.7415
7.250 1.2756 0.01130 0.00632 -0.1173 0.5896 0.7453
7.500 1.2850 0.01148 0.00662 -0.1139 0.5821 0.7493
7.750 1.2948 0.01169 0.00684 -0.1107 0.5705 0.7540
8.000 1.3043 0.01199 0.00715 -0.1075 0.5573 0.7587
8.250 1.3164 0.01235 0.00756 -0.1052 0.5442 0.7638
8.500 1.3276 0.01285 0.00809 -0.1029 0.5297 0.7702
8.750 1.3398 0.01349 0.00877 -0.1012 0.5130 0.7766
9.000 1.3532 0.01426 0.00957 -0.0999 0.4951 0.7840
9.250 1.3658 0.01523 0.01053 -0.0988 0.4751 0.7924
9.500 1.3771 0.01643 0.01172 -0.0979 0.4527 0.8034
9.750 1.3853 0.01807 0.01332 -0.0970 0.4217 0.8176
10.000 1.3905 0.02023 0.01540 -0.0964 0.3831 0.8393
10.250 1.4110 0.02271 0.01786 -0.0996 0.3411 0.8921
10.500 1.4168 0.02568 0.02064 -0.0999 0.2964 1.0000
10.750 1.4131 0.02785 0.02267 -0.0973 0.2680 1.0000
11.000 1.4072 0.03027 0.02491 -0.0946 0.2359 1.0000
11.250 1.3981 0.03301 0.02743 -0.0917 0.2006 1.0000
11.500 1.3938 0.03550 0.02974 -0.0895 0.1703 1.0000
11.750 1.3923 0.03783 0.03195 -0.0875 0.1453 1.0000
12.000 1.3871 0.04053 0.03446 -0.0854 0.1166 1.0000
12.250 1.3860 0.04295 0.03675 -0.0837 0.0933 1.0000
12.500 1.3858 0.04537 0.03908 -0.0822 0.0762 1.0000
12.750 1.3858 0.04782 0.04145 -0.0807 0.0600 1.0000
13.000 1.3876 0.05016 0.04373 -0.0795 0.0492 1.0000
13.250 1.3894 0.05254 0.04607 -0.0783 0.0405 1.0000
13.500 1.3914 0.05494 0.04848 -0.0772 0.0358 1.0000
13.750 1.3976 0.05699 0.05059 -0.0765 0.0322 1.0000
14.000 1.4002 0.05943 0.05304 -0.0756 0.0291 1.0000
14.250 1.4051 0.06168 0.05535 -0.0749 0.0265 1.0000
14.500 1.4092 0.06399 0.05771 -0.0742 0.0244 1.0000
14.750 1.4068 0.06709 0.06084 -0.0733 0.0221 1.0000
15.000 1.4131 0.06925 0.06309 -0.0728 0.0202 1.0000
15.250 1.4157 0.07187 0.06577 -0.0723 0.0190 1.0000
15.500 1.4105 0.07544 0.06938 -0.0716 0.0170 1.0000
15.750 1.4144 0.07796 0.07200 -0.0712 0.0160 1.0000
16.000 1.4168 0.08070 0.07481 -0.0709 0.0148 1.0000
16.250 1.4146 0.08401 0.07816 -0.0706 0.0137 1.0000
16.500 1.4099 0.08772 0.08197 -0.0704 0.0131 1.0000
16.750 1.4111 0.09074 0.08509 -0.0703 0.0124 1.0000
17.000 1.4123 0.09376 0.08820 -0.0703 0.0118 1.0000
17.250 1.4112 0.09712 0.09163 -0.0704 0.0112 1.0000
17.500 1.4087 0.10068 0.09525 -0.0706 0.0107 1.0000
17.750 1.4041 0.10457 0.09921 -0.0709 0.0104 1.0000
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