HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il) Reynolds number: 50,000 Max Cl/Cd: 45.02 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1606-il-50000-n5.txt Download as CSV file: xf-hs1606-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-606 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3644 0.09586 0.08929 -0.0283 1.0000 0.0505
-7.000 -0.3674 0.09310 0.08663 -0.0284 1.0000 0.0470
-6.750 -0.3707 0.09012 0.08372 -0.0311 1.0000 0.0418
-6.500 -0.3695 0.08738 0.08103 -0.0302 1.0000 0.0407
-6.250 -0.3677 0.08454 0.07825 -0.0303 1.0000 0.0398
-6.000 -0.3639 0.08149 0.07524 -0.0312 1.0000 0.0388
-5.750 -0.3574 0.07817 0.07194 -0.0329 1.0000 0.0379
-5.500 -0.3475 0.07451 0.06827 -0.0354 1.0000 0.0370
-5.250 -0.3335 0.07046 0.06419 -0.0389 1.0000 0.0362
-5.000 -0.3149 0.06607 0.05974 -0.0431 1.0000 0.0356
-4.750 -0.2921 0.06161 0.05518 -0.0477 1.0000 0.0358
-4.500 -0.2651 0.05704 0.05046 -0.0528 1.0000 0.0367
-4.250 -0.2322 0.05198 0.04517 -0.0588 1.0000 0.0381
-4.000 -0.1919 0.04606 0.03888 -0.0660 1.0000 0.0394
-3.750 -0.1430 0.03909 0.03123 -0.0742 1.0000 0.0407
-3.500 -0.0896 0.03237 0.02331 -0.0817 1.0000 0.0426
-3.250 -0.0573 0.03039 0.02106 -0.0836 1.0000 0.0483
-3.000 -0.0233 0.02847 0.01860 -0.0853 1.0000 0.0619
-2.750 0.0066 0.02765 0.01747 -0.0861 1.0000 0.0938
-2.500 0.0302 0.02791 0.01770 -0.0858 1.0000 0.1265
-2.250 0.0578 0.02745 0.01685 -0.0861 1.0000 0.1480
-2.000 0.0894 0.02679 0.01584 -0.0871 0.9985 0.1619
-1.750 0.1246 0.02646 0.01524 -0.0890 0.9951 0.1804
-1.500 0.1592 0.02605 0.01453 -0.0905 0.9914 0.1957
-1.250 0.1942 0.02585 0.01407 -0.0922 0.9872 0.2179
-1.000 0.2311 0.02560 0.01368 -0.0943 0.9836 0.2387
-0.750 0.2642 0.02541 0.01334 -0.0957 0.9784 0.2625
-0.500 0.2996 0.02524 0.01313 -0.0976 0.9735 0.2888
-0.250 0.3370 0.02506 0.01301 -0.0999 0.9693 0.3187
0.000 0.3691 0.02488 0.01298 -0.1013 0.9630 0.3536
0.250 0.4069 0.02439 0.01304 -0.1039 0.9586 0.4499
0.500 0.4278 0.02356 0.01303 -0.1024 0.9496 1.0000
0.750 0.4655 0.02395 0.01317 -0.1046 0.9436 1.0000
1.000 0.4956 0.02432 0.01339 -0.1053 0.9349 1.0000
1.250 0.5317 0.02464 0.01360 -0.1072 0.9269 1.0000
1.500 0.5718 0.02482 0.01371 -0.1095 0.9168 1.0000
1.750 0.6089 0.02490 0.01378 -0.1111 0.9042 1.0000
2.000 0.6445 0.02497 0.01389 -0.1123 0.8913 1.0000
2.250 0.6777 0.02508 0.01405 -0.1131 0.8791 1.0000
2.500 0.7101 0.02521 0.01425 -0.1137 0.8672 1.0000
2.750 0.7424 0.02529 0.01443 -0.1142 0.8553 1.0000
3.000 0.7747 0.02533 0.01467 -0.1146 0.8429 1.0000
3.250 0.8063 0.02532 0.01482 -0.1147 0.8297 1.0000
3.500 0.8366 0.02528 0.01496 -0.1145 0.8150 1.0000
3.750 0.8662 0.02520 0.01507 -0.1140 0.7990 1.0000
4.000 0.8964 0.02501 0.01518 -0.1134 0.7820 1.0000
4.250 0.9245 0.02483 0.01524 -0.1124 0.7625 1.0000
4.500 0.9503 0.02467 0.01534 -0.1109 0.7396 1.0000
4.750 0.9744 0.02454 0.01548 -0.1091 0.7129 1.0000
5.000 0.9990 0.02431 0.01551 -0.1072 0.6806 1.0000
5.250 1.0226 0.02364 0.01496 -0.1041 0.6188 1.0000
5.500 1.0475 0.02327 0.01380 -0.1003 0.4963 1.0000
5.750 1.0601 0.02443 0.01436 -0.0970 0.3974 1.0000
6.000 1.0713 0.02586 0.01538 -0.0941 0.3183 1.0000
6.250 1.0798 0.02770 0.01670 -0.0913 0.2102 1.0000
6.500 1.0873 0.03020 0.01839 -0.0888 0.1260 1.0000
6.750 1.1007 0.03222 0.02025 -0.0869 0.1005 1.0000
7.000 1.1158 0.03405 0.02212 -0.0850 0.0896 1.0000
7.250 1.1338 0.03575 0.02402 -0.0833 0.0822 1.0000
7.500 1.1517 0.03768 0.02597 -0.0818 0.0756 1.0000
7.750 1.1724 0.03937 0.02793 -0.0806 0.0678 1.0000
8.000 1.1963 0.04170 0.03023 -0.0799 0.0632 1.0000
8.250 1.2257 0.04412 0.03308 -0.0794 0.0600 1.0000
8.500 1.2522 0.04698 0.03632 -0.0787 0.0570 1.0000
8.750 1.2707 0.04969 0.03934 -0.0777 0.0528 1.0000
9.000 1.2856 0.05305 0.04306 -0.0763 0.0494 1.0000
9.250 1.2968 0.05670 0.04733 -0.0740 0.0479 1.0000
9.500 1.3023 0.06065 0.05184 -0.0715 0.0467 1.0000
9.750 1.3019 0.06470 0.05640 -0.0686 0.0458 1.0000
10.000 1.2961 0.06856 0.06069 -0.0656 0.0446 1.0000
10.250 1.2870 0.07212 0.06459 -0.0626 0.0433 1.0000
10.500 1.2763 0.07536 0.06804 -0.0596 0.0419 1.0000
10.750 1.2688 0.07867 0.07146 -0.0575 0.0403 1.0000
11.000 1.2562 0.08282 0.07576 -0.0557 0.0394 1.0000
11.250 1.2386 0.08741 0.08056 -0.0545 0.0391 1.0000
11.500 1.2177 0.09222 0.08562 -0.0541 0.0392 1.0000
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Polar data table (+)
Polar graphs
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