FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 73-K-170/22 (fx73k170-il) Reynolds number: 500,000 Max Cl/Cd: 109.95 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73k170-il-500000-n5.txt Download as CSV file: xf-fx73k170-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1645 0.09571 0.09209 -0.1158 0.7842 0.0075
-12.750 -0.2985 0.05963 0.05581 -0.1354 0.7840 0.0069
-12.500 -0.3277 0.05055 0.04652 -0.1429 0.7822 0.0066
-12.250 -0.3412 0.04520 0.04096 -0.1473 0.7801 0.0068
-12.000 -0.3506 0.04098 0.03654 -0.1502 0.7781 0.0068
-11.750 -0.3600 0.03707 0.03238 -0.1524 0.7759 0.0069
-11.500 -0.3674 0.03357 0.02862 -0.1537 0.7739 0.0068
-11.250 -0.3605 0.03185 0.02676 -0.1543 0.7720 0.0070
-11.000 -0.3614 0.02939 0.02410 -0.1542 0.7697 0.0069
-10.750 -0.3556 0.02774 0.02230 -0.1539 0.7673 0.0071
-10.500 -0.3493 0.02621 0.02058 -0.1531 0.7651 0.0073
-10.250 -0.3418 0.02504 0.01925 -0.1520 0.7629 0.0074
-10.000 -0.3361 0.02382 0.01788 -0.1503 0.7609 0.0074
-9.750 -0.3244 0.02305 0.01695 -0.1489 0.7588 0.0075
-9.500 -0.3117 0.02186 0.01561 -0.1476 0.7570 0.0075
-9.250 -0.2981 0.02081 0.01447 -0.1463 0.7549 0.0077
-9.000 -0.2835 0.01979 0.01336 -0.1451 0.7529 0.0078
-8.750 -0.2664 0.01900 0.01249 -0.1441 0.7508 0.0079
-8.500 -0.2484 0.01828 0.01171 -0.1432 0.7488 0.0080
-8.250 -0.2293 0.01763 0.01098 -0.1424 0.7468 0.0081
-8.000 -0.2098 0.01698 0.01026 -0.1416 0.7449 0.0083
-7.750 -0.1890 0.01643 0.00962 -0.1410 0.7431 0.0084
-7.500 -0.1684 0.01588 0.00903 -0.1403 0.7411 0.0087
-7.250 -0.1474 0.01536 0.00847 -0.1397 0.7389 0.0089
-7.000 -0.1255 0.01488 0.00793 -0.1391 0.7368 0.0094
-6.750 -0.1031 0.01442 0.00742 -0.1386 0.7346 0.0097
-6.500 -0.0798 0.01401 0.00694 -0.1382 0.7325 0.0101
-6.250 -0.0567 0.01354 0.00642 -0.1378 0.7306 0.0107
-6.000 -0.0324 0.01317 0.00600 -0.1376 0.7286 0.0113
-5.750 -0.0076 0.01287 0.00565 -0.1374 0.7265 0.0121
-5.500 0.0170 0.01257 0.00532 -0.1371 0.7242 0.0132
-5.250 0.0418 0.01227 0.00502 -0.1369 0.7218 0.0152
-5.000 0.0671 0.01200 0.00474 -0.1367 0.7195 0.0182
-4.750 0.0924 0.01170 0.00445 -0.1366 0.7173 0.0258
-4.500 0.1181 0.01143 0.00419 -0.1365 0.7152 0.0372
-4.250 0.1439 0.01116 0.00395 -0.1365 0.7132 0.0545
-3.750 0.1921 0.01037 0.00352 -0.1360 0.7080 0.1473
-3.500 0.2143 0.00975 0.00327 -0.1357 0.7054 0.2487
-3.250 0.2350 0.00902 0.00299 -0.1350 0.7029 0.3819
-3.000 0.2589 0.00869 0.00287 -0.1346 0.7006 0.4583
-2.750 0.2848 0.00857 0.00283 -0.1344 0.6983 0.5050
-2.500 0.3109 0.00855 0.00288 -0.1342 0.6957 0.5394
-2.250 0.3377 0.00858 0.00292 -0.1340 0.6929 0.5635
-2.000 0.3647 0.00863 0.00295 -0.1340 0.6902 0.5778
-1.750 0.3921 0.00865 0.00295 -0.1339 0.6875 0.5864
-1.500 0.4197 0.00868 0.00291 -0.1340 0.6849 0.5932
-1.250 0.4471 0.00872 0.00290 -0.1340 0.6823 0.5995
-1.000 0.4739 0.00875 0.00293 -0.1339 0.6791 0.6041
-0.750 0.5010 0.00879 0.00294 -0.1339 0.6762 0.6090
-0.500 0.5283 0.00883 0.00292 -0.1340 0.6735 0.6135
-0.250 0.5554 0.00884 0.00292 -0.1340 0.6707 0.6164
0.000 0.5827 0.00888 0.00292 -0.1340 0.6683 0.6196
0.250 0.6092 0.00891 0.00297 -0.1339 0.6652 0.6229
0.500 0.6359 0.00895 0.00299 -0.1338 0.6620 0.6261
0.750 0.6627 0.00900 0.00300 -0.1338 0.6590 0.6290
1.000 0.6895 0.00903 0.00302 -0.1338 0.6563 0.6313
1.250 0.7164 0.00907 0.00305 -0.1338 0.6538 0.6335
1.500 0.7422 0.00911 0.00312 -0.1335 0.6504 0.6356
1.750 0.7682 0.00916 0.00318 -0.1333 0.6468 0.6381
2.000 0.7943 0.00922 0.00322 -0.1332 0.6436 0.6406
2.250 0.8207 0.00928 0.00325 -0.1331 0.6405 0.6428
2.500 0.8462 0.00935 0.00332 -0.1329 0.6369 0.6453
2.750 0.8713 0.00939 0.00341 -0.1325 0.6333 0.6473
3.000 0.8964 0.00945 0.00349 -0.1322 0.6295 0.6492
3.250 0.9218 0.00953 0.00357 -0.1319 0.6260 0.6513
3.500 0.9467 0.00960 0.00367 -0.1315 0.6225 0.6537
3.750 0.9710 0.00968 0.00378 -0.1310 0.6186 0.6562
4.000 0.9950 0.00977 0.00389 -0.1305 0.6143 0.6586
4.250 1.0195 0.00987 0.00397 -0.1301 0.6105 0.6606
4.500 1.0429 0.00995 0.00411 -0.1294 0.6064 0.6627
4.750 1.0657 0.01003 0.00426 -0.1286 0.6020 0.6649
5.000 1.0881 0.01013 0.00438 -0.1278 0.5972 0.6673
5.250 1.1102 0.01025 0.00452 -0.1269 0.5925 0.6698
5.500 1.1302 0.01036 0.00468 -0.1256 0.5861 0.6722
5.750 1.1502 0.01049 0.00483 -0.1242 0.5808 0.6746
6.000 1.1666 0.01061 0.00499 -0.1222 0.5738 0.6770
6.250 1.1829 0.01076 0.00517 -0.1201 0.5669 0.6795
6.500 1.1991 0.01095 0.00541 -0.1181 0.5589 0.6821
6.750 1.2125 0.01121 0.00567 -0.1155 0.5490 0.6850
7.000 1.2284 0.01145 0.00597 -0.1136 0.5401 0.6877
7.250 1.2406 0.01180 0.00632 -0.1110 0.5280 0.6906
7.500 1.2507 0.01225 0.00677 -0.1082 0.5138 0.6936
7.750 1.2528 0.01301 0.00747 -0.1044 0.4911 0.6969
8.000 1.2646 0.01364 0.00811 -0.1024 0.4778 0.7004
8.250 1.2656 0.01479 0.00917 -0.0990 0.4509 0.7040
8.500 1.2572 0.01659 0.01077 -0.0948 0.4131 0.7075
8.750 1.2584 0.01809 0.01218 -0.0921 0.3846 0.7110
9.000 1.2601 0.01969 0.01367 -0.0897 0.3559 0.7151
9.250 1.2582 0.02154 0.01538 -0.0870 0.3236 0.7191
9.500 1.2618 0.02312 0.01687 -0.0850 0.2977 0.7235
9.750 1.2664 0.02475 0.01843 -0.0833 0.2729 0.7281
10.000 1.2702 0.02648 0.02008 -0.0817 0.2484 0.7338
10.500 1.2803 0.03005 0.02350 -0.0790 0.1986 0.7467
10.750 1.2817 0.03221 0.02552 -0.0775 0.1684 0.7542
11.000 1.2863 0.03427 0.02750 -0.0765 0.1436 0.7626
11.250 1.2952 0.03605 0.02925 -0.0759 0.1248 0.7728
11.500 1.3014 0.03819 0.03134 -0.0753 0.1036 0.7861
11.750 1.3096 0.04035 0.03348 -0.0752 0.0831 0.8044
12.000 1.3176 0.04299 0.03607 -0.0758 0.0595 0.8348
12.250 1.3529 0.04589 0.03910 -0.0820 0.0436 0.9141
13.250 1.3829 0.05390 0.04713 -0.0793 0.0233 1.0000
13.750 1.3987 0.05770 0.05102 -0.0780 0.0199 1.0000
14.000 1.4045 0.05982 0.05318 -0.0773 0.0183 1.0000
14.250 1.4108 0.06191 0.05533 -0.0767 0.0170 1.0000
14.500 1.4175 0.06401 0.05748 -0.0762 0.0148 1.0000
14.750 1.4235 0.06618 0.05971 -0.0757 0.0140 1.0000
15.000 1.4280 0.06856 0.06215 -0.0752 0.0126 1.0000
15.250 1.4340 0.07080 0.06446 -0.0748 0.0118 1.0000
15.500 1.4380 0.07326 0.06697 -0.0744 0.0104 1.0000
15.750 1.4412 0.07581 0.06958 -0.0740 0.0095 1.0000
16.000 1.4448 0.07838 0.07223 -0.0737 0.0087 1.0000
16.250 1.4478 0.08105 0.07496 -0.0734 0.0081 1.0000
16.500 1.4492 0.08395 0.07792 -0.0732 0.0074 1.0000
16.750 1.4508 0.08684 0.08089 -0.0731 0.0070 1.0000
17.000 1.4521 0.08980 0.08394 -0.0730 0.0065 1.0000
17.250 1.4535 0.09276 0.08700 -0.0730 0.0062 1.0000
17.500 1.4530 0.09599 0.09031 -0.0731 0.0058 1.0000
17.750 1.4524 0.09931 0.09371 -0.0733 0.0055 1.0000
18.000 1.4522 0.10257 0.09706 -0.0736 0.0055 1.0000
18.250 1.4491 0.10630 0.10088 -0.0740 0.0050 1.0000
18.500 1.4474 0.10989 0.10457 -0.0745 0.0049 1.0000
18.750 1.4455 0.11347 0.10826 -0.0752 0.0047 1.0000
19.000 1.4435 0.11712 0.11201 -0.0759 0.0046 1.0000
19.250 1.4405 0.12097 0.11596 -0.0768 0.0044 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 73-K-170/22 (fx73k170-il)