HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il) Reynolds number: 50,000 Max Cl/Cd: 25.22 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1620-il-50000-n5.txt Download as CSV file: xf-hs1620-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-620 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5001 0.11161 0.10367 -0.0406 1.0000 0.1162
-9.750 -0.5433 0.10358 0.09571 -0.0419 1.0000 0.1173
-9.500 -0.6378 0.09070 0.08283 -0.0436 1.0000 0.1173
-9.250 -0.7190 0.07950 0.07135 -0.0418 0.9999 0.1180
-9.000 -0.7395 0.07078 0.06213 -0.0445 0.9939 0.1208
-8.750 -0.7150 0.06982 0.06114 -0.0456 0.9892 0.1233
-8.500 -0.7066 0.06563 0.05662 -0.0470 0.9836 0.1267
-8.250 -0.7008 0.06036 0.05075 -0.0485 0.9782 0.1310
-8.000 -0.6742 0.05973 0.05014 -0.0493 0.9726 0.1339
-7.500 -0.6346 0.05484 0.04455 -0.0512 0.9618 0.1428
-7.250 -0.6053 0.05421 0.04390 -0.0525 0.9570 0.1466
-7.000 -0.5833 0.05226 0.04157 -0.0532 0.9512 0.1521
-6.750 -0.5570 0.05127 0.04046 -0.0540 0.9454 0.1565
-6.500 -0.5251 0.05048 0.03955 -0.0557 0.9414 0.1618
-6.250 -0.5054 0.04901 0.03771 -0.0555 0.9344 0.1679
-6.000 -0.4750 0.04867 0.03743 -0.0566 0.9293 0.1725
-5.750 -0.4461 0.04778 0.03626 -0.0577 0.9242 0.1795
-5.500 -0.4221 0.04713 0.03553 -0.0577 0.9174 0.1850
-5.250 -0.3897 0.04665 0.03498 -0.0592 0.9129 0.1917
-5.000 -0.3649 0.04594 0.03399 -0.0594 0.9065 0.1991
-4.750 -0.3374 0.04560 0.03372 -0.0599 0.9003 0.2049
-4.250 -0.2818 0.04470 0.03258 -0.0610 0.8886 0.2199
-4.000 -0.2514 0.04435 0.03217 -0.0620 0.8831 0.2280
-3.750 -0.2147 0.04385 0.03151 -0.0640 0.8794 0.2373
-3.500 -0.1974 0.04372 0.03143 -0.0626 0.8705 0.2438
-3.250 -0.1642 0.04341 0.03094 -0.0640 0.8656 0.2538
-3.000 -0.1347 0.04310 0.03071 -0.0647 0.8600 0.2619
-2.750 -0.1112 0.04298 0.03056 -0.0643 0.8522 0.2708
-2.500 -0.0758 0.04266 0.03020 -0.0660 0.8477 0.2810
-2.250 -0.0523 0.04261 0.03019 -0.0656 0.8401 0.2905
-2.000 -0.0232 0.04249 0.03000 -0.0661 0.8334 0.3012
-1.750 0.0142 0.04215 0.02973 -0.0680 0.8293 0.3137
-1.500 0.0330 0.04234 0.02990 -0.0668 0.8199 0.3241
-1.250 0.0655 0.04210 0.02976 -0.0678 0.8141 0.3381
-1.000 0.1049 0.04164 0.02938 -0.0699 0.8102 0.3555
-0.750 0.1194 0.04196 0.02978 -0.0681 0.7990 0.3708
-0.500 0.1568 0.04137 0.02939 -0.0697 0.7936 0.3974
-0.250 0.1790 0.04113 0.02940 -0.0688 0.7826 0.4306
0.000 0.2143 0.03995 0.02885 -0.0694 0.7753 0.5167
0.250 0.2337 0.03914 0.02895 -0.0662 0.7650 0.7184
0.500 0.3045 0.03854 0.02868 -0.0723 0.7563 0.9760
1.000 0.3673 0.03810 0.02785 -0.0734 0.7370 1.0000
1.250 0.4105 0.03722 0.02676 -0.0753 0.7323 1.0000
1.500 0.4198 0.03778 0.02723 -0.0724 0.7177 1.0000
1.750 0.4627 0.03689 0.02617 -0.0742 0.7123 1.0000
2.000 0.4738 0.03742 0.02663 -0.0715 0.6978 1.0000
2.250 0.5168 0.03652 0.02558 -0.0733 0.6918 1.0000
2.500 0.5290 0.03702 0.02602 -0.0707 0.6769 1.0000
2.750 0.5738 0.03601 0.02487 -0.0727 0.6704 1.0000
3.000 0.5848 0.03657 0.02539 -0.0699 0.6546 1.0000
3.250 0.6146 0.03627 0.02500 -0.0698 0.6434 1.0000
3.500 0.6429 0.03601 0.02465 -0.0694 0.6308 1.0000
3.750 0.6596 0.03633 0.02493 -0.0674 0.6151 1.0000
4.000 0.6907 0.03597 0.02447 -0.0674 0.6027 1.0000
4.250 0.7170 0.03583 0.02425 -0.0668 0.5882 1.0000
4.500 0.7332 0.03622 0.02458 -0.0648 0.5709 1.0000
4.750 0.7538 0.03644 0.02472 -0.0634 0.5544 1.0000
5.000 0.7794 0.03644 0.02461 -0.0628 0.5391 1.0000
5.250 0.8105 0.03618 0.02420 -0.0628 0.5246 1.0000
5.500 0.8301 0.03657 0.02450 -0.0614 0.5080 1.0000
5.750 0.8499 0.03702 0.02485 -0.0602 0.4922 1.0000
6.000 0.8739 0.03731 0.02502 -0.0595 0.4783 1.0000
6.250 0.9028 0.03739 0.02490 -0.0595 0.4656 1.0000
6.500 0.9181 0.03823 0.02570 -0.0578 0.4518 1.0000
6.750 0.9421 0.03868 0.02602 -0.0573 0.4405 1.0000
7.000 0.9628 0.03932 0.02658 -0.0564 0.4293 1.0000
7.250 0.9834 0.04003 0.02721 -0.0556 0.4192 1.0000
7.500 1.0047 0.04070 0.02781 -0.0549 0.4094 1.0000
7.750 1.0265 0.04142 0.02847 -0.0543 0.4008 1.0000
8.000 1.0442 0.04234 0.02938 -0.0532 0.3921 1.0000
8.250 1.0755 0.04264 0.02952 -0.0538 0.3848 1.0000
8.500 1.0834 0.04409 0.03109 -0.0516 0.3767 1.0000
8.750 1.1073 0.04476 0.03171 -0.0514 0.3696 1.0000
9.000 1.1311 0.04551 0.03240 -0.0512 0.3632 1.0000
9.250 1.1382 0.04705 0.03407 -0.0490 0.3563 1.0000
9.500 1.1615 0.04779 0.03477 -0.0487 0.3500 1.0000
9.750 1.1872 0.04851 0.03542 -0.0488 0.3444 1.0000
10.000 1.1865 0.05053 0.03764 -0.0459 0.3383 1.0000
10.250 1.2012 0.05176 0.03890 -0.0447 0.3325 1.0000
10.500 1.2378 0.05190 0.03890 -0.0460 0.3273 1.0000
10.750 1.2301 0.05442 0.04164 -0.0426 0.3222 1.0000
11.000 1.2272 0.05676 0.04416 -0.0399 0.3168 1.0000
11.250 1.2434 0.05795 0.04536 -0.0391 0.3118 1.0000
11.500 1.2827 0.05788 0.04513 -0.0405 0.3072 1.0000
11.750 1.2470 0.06245 0.05008 -0.0353 0.3025 1.0000
12.000 1.2275 0.06637 0.05423 -0.0322 0.2974 1.0000
12.250 1.2389 0.06796 0.05586 -0.0312 0.2928 1.0000
12.500 1.2874 0.06678 0.05452 -0.0327 0.2890 1.0000
12.750 1.1553 0.08165 0.07006 -0.0260 0.2824 1.0000
13.000 1.0866 0.09332 0.08199 -0.0256 0.2746 1.0000
13.250 1.1301 0.09084 0.07946 -0.0249 0.2724 1.0000
13.500 1.1974 0.08594 0.07442 -0.0246 0.2706 1.0000
13.750 0.9983 0.11787 0.10688 -0.0299 0.2536 1.0000
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Polar data table (+)
Polar graphs
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