HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.69 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1712-il-1000000-n5.txt Download as CSV file: xf-hs1712-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAM-STD HS1-712 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.3410 0.16130 0.15932 -0.0565 0.9917 0.0064
-15.000 -0.3329 0.15800 0.15602 -0.0583 0.9909 0.0066
-14.000 -0.8265 0.03275 0.02965 -0.1378 0.9773 0.0092
-13.750 -0.8120 0.02927 0.02595 -0.1405 0.9759 0.0093
-13.500 -0.7917 0.02706 0.02356 -0.1422 0.9749 0.0094
-13.250 -0.7686 0.02534 0.02169 -0.1437 0.9740 0.0096
-13.000 -0.7438 0.02389 0.02010 -0.1450 0.9733 0.0098
-12.750 -0.7178 0.02261 0.01868 -0.1462 0.9725 0.0099
-12.500 -0.6908 0.02149 0.01743 -0.1474 0.9718 0.0101
-12.250 -0.6632 0.02050 0.01632 -0.1485 0.9711 0.0103
-12.000 -0.6407 0.01971 0.01542 -0.1482 0.9686 0.0104
-11.750 -0.6149 0.01895 0.01456 -0.1486 0.9669 0.0106
-11.500 -0.5880 0.01807 0.01358 -0.1492 0.9653 0.0108
-11.250 -0.5601 0.01728 0.01270 -0.1500 0.9638 0.0111
-11.000 -0.5312 0.01663 0.01198 -0.1508 0.9624 0.0114
-10.750 -0.5018 0.01604 0.01133 -0.1516 0.9610 0.0116
-10.500 -0.4715 0.01549 0.01071 -0.1526 0.9597 0.0119
-10.250 -0.4408 0.01497 0.01011 -0.1536 0.9584 0.0122
-10.000 -0.4140 0.01453 0.00961 -0.1537 0.9559 0.0126
-9.750 -0.3862 0.01411 0.00912 -0.1540 0.9537 0.0129
-9.500 -0.3576 0.01371 0.00866 -0.1544 0.9519 0.0131
-9.250 -0.3285 0.01324 0.00814 -0.1550 0.9501 0.0135
-9.000 -0.2988 0.01283 0.00768 -0.1556 0.9482 0.0140
-8.750 -0.2683 0.01247 0.00729 -0.1564 0.9463 0.0145
-8.500 -0.2375 0.01215 0.00692 -0.1572 0.9447 0.0151
-8.250 -0.2085 0.01186 0.00658 -0.1576 0.9424 0.0156
-8.000 -0.1800 0.01158 0.00626 -0.1579 0.9396 0.0161
-7.750 -0.1509 0.01123 0.00589 -0.1583 0.9368 0.0168
-7.500 -0.1211 0.01094 0.00557 -0.1589 0.9343 0.0174
-7.250 -0.0907 0.01068 0.00528 -0.1595 0.9318 0.0182
-7.000 -0.0599 0.01044 0.00499 -0.1602 0.9294 0.0190
-6.750 -0.0308 0.01017 0.00471 -0.1606 0.9260 0.0200
-6.500 -0.0016 0.00994 0.00446 -0.1609 0.9211 0.0211
-6.250 0.0287 0.00972 0.00420 -0.1615 0.9153 0.0221
-6.000 0.0584 0.00951 0.00399 -0.1619 0.9086 0.0237
-5.750 0.0881 0.00934 0.00379 -0.1623 0.8985 0.0256
-5.500 0.1178 0.00924 0.00368 -0.1627 0.8860 0.0281
-5.250 0.1473 0.00918 0.00357 -0.1630 0.8708 0.0309
-5.000 0.1764 0.00916 0.00346 -0.1632 0.8553 0.0333
-4.750 0.2045 0.00917 0.00335 -0.1631 0.8334 0.0350
-4.500 0.2317 0.00924 0.00327 -0.1629 0.8069 0.0365
-4.250 0.2588 0.00925 0.00315 -0.1627 0.7903 0.0377
-4.000 0.2870 0.00921 0.00304 -0.1628 0.7770 0.0390
-3.750 0.3122 0.00930 0.00294 -0.1622 0.7250 0.0400
-3.500 0.3378 0.00945 0.00292 -0.1617 0.6982 0.0409
-3.250 0.3649 0.00948 0.00284 -0.1616 0.6721 0.0420
-3.000 0.3920 0.00951 0.00277 -0.1615 0.6493 0.0430
-2.750 0.4197 0.00954 0.00271 -0.1615 0.6304 0.0440
-2.500 0.4476 0.00956 0.00265 -0.1615 0.6140 0.0451
-2.250 0.4750 0.00962 0.00263 -0.1615 0.5929 0.0462
-2.000 0.5020 0.00972 0.00263 -0.1613 0.5708 0.0477
-1.750 0.5295 0.00979 0.00264 -0.1613 0.5571 0.0492
-1.500 0.5576 0.00981 0.00264 -0.1614 0.5365 0.0579
-1.250 0.5831 0.01004 0.00269 -0.1609 0.4982 0.0612
-1.000 0.6081 0.01033 0.00279 -0.1604 0.4533 0.0653
-0.750 0.6319 0.01072 0.00294 -0.1597 0.3929 0.0748
-0.500 0.6571 0.01100 0.00306 -0.1593 0.3536 0.0883
0.000 0.7125 0.01111 0.00320 -0.1594 0.3383 0.1218
0.250 0.7404 0.01116 0.00327 -0.1595 0.3324 0.1389
0.500 0.7678 0.01124 0.00337 -0.1595 0.3258 0.1592
0.750 0.7958 0.01127 0.00344 -0.1596 0.3204 0.1743
1.000 0.8232 0.01136 0.00353 -0.1596 0.3112 0.1898
1.250 0.8505 0.01145 0.00363 -0.1595 0.3014 0.2083
1.500 0.8772 0.01158 0.00373 -0.1594 0.2879 0.2251
1.750 0.9037 0.01172 0.00385 -0.1592 0.2747 0.2423
2.000 0.9303 0.01184 0.00397 -0.1591 0.2621 0.2711
2.250 0.9575 0.01177 0.00419 -0.1594 0.2459 0.4328
2.750 1.0030 0.01128 0.00477 -0.1576 0.2146 0.9185
3.000 1.0198 0.01137 0.00482 -0.1550 0.1971 1.0000
3.250 1.0439 0.01172 0.00504 -0.1544 0.1777 1.0000
3.500 1.0681 0.01206 0.00528 -0.1537 0.1609 1.0000
3.750 1.0918 0.01241 0.00552 -0.1530 0.1442 1.0000
4.000 1.1155 0.01276 0.00578 -0.1523 0.1292 1.0000
4.250 1.1372 0.01324 0.00611 -0.1512 0.1059 1.0000
4.500 1.1583 0.01374 0.00648 -0.1499 0.0794 1.0000
4.750 1.1816 0.01406 0.00674 -0.1491 0.0761 1.0000
5.000 1.2052 0.01434 0.00699 -0.1484 0.0732 1.0000
5.250 1.2291 0.01458 0.00723 -0.1477 0.0722 1.0000
5.500 1.2525 0.01484 0.00749 -0.1469 0.0711 1.0000
5.750 1.2754 0.01511 0.00775 -0.1460 0.0700 1.0000
6.000 1.2966 0.01540 0.00804 -0.1447 0.0690 1.0000
6.250 1.3174 0.01571 0.00836 -0.1434 0.0681 1.0000
6.500 1.3381 0.01604 0.00870 -0.1420 0.0672 1.0000
6.750 1.3589 0.01636 0.00903 -0.1408 0.0666 1.0000
7.000 1.3800 0.01666 0.00935 -0.1395 0.0661 1.0000
7.250 1.4011 0.01697 0.00968 -0.1384 0.0652 1.0000
7.500 1.4220 0.01730 0.01002 -0.1372 0.0638 1.0000
7.750 1.4425 0.01765 0.01040 -0.1359 0.0623 1.0000
8.000 1.4624 0.01804 0.01079 -0.1345 0.0608 1.0000
8.250 1.4822 0.01844 0.01121 -0.1332 0.0600 1.0000
8.500 1.5019 0.01885 0.01163 -0.1318 0.0592 1.0000
8.750 1.5208 0.01929 0.01208 -0.1304 0.0582 1.0000
9.000 1.5394 0.01975 0.01256 -0.1289 0.0572 1.0000
9.250 1.5580 0.02023 0.01304 -0.1274 0.0562 1.0000
9.500 1.5762 0.02072 0.01356 -0.1259 0.0553 1.0000
9.750 1.5941 0.02122 0.01409 -0.1243 0.0548 1.0000
10.000 1.6117 0.02176 0.01466 -0.1228 0.0540 1.0000
10.250 1.6284 0.02235 0.01527 -0.1211 0.0528 1.0000
10.500 1.6435 0.02304 0.01598 -0.1192 0.0514 1.0000
10.750 1.6585 0.02374 0.01671 -0.1173 0.0501 1.0000
11.000 1.6765 0.02424 0.01727 -0.1160 0.0491 1.0000
11.250 1.6931 0.02484 0.01791 -0.1144 0.0476 1.0000
11.500 1.7084 0.02553 0.01864 -0.1127 0.0454 1.0000
11.750 1.7251 0.02614 0.01928 -0.1113 0.0386 1.0000
12.000 1.7341 0.02726 0.02031 -0.1087 0.0331 1.0000
12.250 1.7454 0.02825 0.02133 -0.1066 0.0311 1.0000
12.500 1.7557 0.02934 0.02246 -0.1044 0.0298 1.0000
12.750 1.7648 0.03053 0.02370 -0.1021 0.0284 1.0000
13.000 1.7763 0.03156 0.02478 -0.1002 0.0276 1.0000
13.250 1.7871 0.03265 0.02594 -0.0983 0.0267 1.0000
13.500 1.7964 0.03389 0.02724 -0.0963 0.0259 1.0000
13.750 1.8045 0.03527 0.02867 -0.0943 0.0250 1.0000
14.000 1.8127 0.03668 0.03014 -0.0924 0.0243 1.0000
14.250 1.8221 0.03802 0.03155 -0.0907 0.0236 1.0000
14.500 1.8303 0.03951 0.03311 -0.0890 0.0227 1.0000
14.750 1.8368 0.04118 0.03484 -0.0873 0.0218 1.0000
15.000 1.8421 0.04302 0.03673 -0.0856 0.0209 1.0000
15.250 1.8482 0.04484 0.03862 -0.0841 0.0201 1.0000
15.500 1.8530 0.04682 0.04067 -0.0827 0.0190 1.0000
15.750 1.8562 0.04903 0.04294 -0.0812 0.0181 1.0000
16.000 1.8591 0.05135 0.04533 -0.0800 0.0172 1.0000
16.250 1.8613 0.05384 0.04790 -0.0789 0.0163 1.0000
16.500 1.8618 0.05657 0.05070 -0.0779 0.0156 1.0000
16.750 1.8612 0.05949 0.05369 -0.0770 0.0148 1.0000
17.000 1.8607 0.06247 0.05676 -0.0763 0.0143 1.0000
17.250 1.8585 0.06573 0.06010 -0.0757 0.0136 1.0000
17.500 1.8550 0.06921 0.06368 -0.0753 0.0131 1.0000
17.750 1.8496 0.07301 0.06756 -0.0750 0.0126 1.0000
18.000 1.8442 0.07685 0.07151 -0.0749 0.0122 1.0000
18.250 1.8379 0.08092 0.07568 -0.0750 0.0118 1.0000
18.500 1.8300 0.08528 0.08015 -0.0753 0.0115 1.0000
18.750 1.8205 0.08995 0.08492 -0.0758 0.0112 1.0000
19.000 1.8096 0.09492 0.09001 -0.0766 0.0109 1.0000
19.250 1.7974 0.10014 0.09534 -0.0776 0.0106 1.0000
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Polar data table (+)
Polar graphs
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