HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.69 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1712-il-1000000.txt Download as CSV file: xf-hs1712-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3046 0.14055 0.13870 -0.0557 0.9923 0.0141
-12.500 -0.2970 0.13719 0.13535 -0.0573 0.9912 0.0146
-12.250 -0.7083 0.03325 0.03039 -0.1259 0.9780 0.0125
-12.000 -0.6890 0.02993 0.02679 -0.1289 0.9764 0.0127
-11.750 -0.6639 0.02765 0.02428 -0.1313 0.9754 0.0130
-11.500 -0.6356 0.02594 0.02237 -0.1335 0.9746 0.0131
-11.250 -0.6089 0.02312 0.01924 -0.1363 0.9739 0.0135
-11.000 -0.5780 0.02164 0.01762 -0.1385 0.9734 0.0138
-10.750 -0.5456 0.02071 0.01661 -0.1404 0.9729 0.0142
-10.500 -0.5123 0.01984 0.01566 -0.1424 0.9726 0.0145
-10.250 -0.4790 0.01898 0.01468 -0.1443 0.9722 0.0149
-10.000 -0.4461 0.01819 0.01377 -0.1460 0.9720 0.0154
-9.750 -0.4130 0.01749 0.01296 -0.1477 0.9717 0.0157
-9.500 -0.3797 0.01673 0.01206 -0.1495 0.9715 0.0161
-9.250 -0.3646 0.01591 0.01117 -0.1472 0.9664 0.0166
-9.000 -0.3335 0.01534 0.01056 -0.1483 0.9654 0.0171
-8.750 -0.3005 0.01483 0.00999 -0.1498 0.9646 0.0177
-8.500 -0.2665 0.01430 0.00939 -0.1514 0.9640 0.0183
-8.250 -0.2323 0.01387 0.00889 -0.1530 0.9634 0.0189
-8.000 -0.1991 0.01314 0.00809 -0.1546 0.9628 0.0198
-7.750 -0.1658 0.01270 0.00763 -0.1560 0.9621 0.0207
-7.500 -0.1326 0.01230 0.00718 -0.1573 0.9614 0.0216
-7.250 -0.0992 0.01185 0.00666 -0.1587 0.9607 0.0225
-7.000 -0.0657 0.01142 0.00623 -0.1601 0.9599 0.0238
-6.750 -0.0322 0.01112 0.00590 -0.1614 0.9590 0.0252
-6.500 -0.0037 0.01086 0.00564 -0.1616 0.9563 0.0267
-6.250 0.0239 0.01070 0.00549 -0.1614 0.9526 0.0281
-6.000 0.0555 0.01047 0.00524 -0.1622 0.9499 0.0298
-5.750 0.0880 0.01033 0.00510 -0.1631 0.9474 0.0316
-5.500 0.1205 0.01013 0.00487 -0.1641 0.9451 0.0336
-5.250 0.1498 0.01000 0.00472 -0.1643 0.9418 0.0359
-5.000 0.1781 0.00974 0.00445 -0.1645 0.9378 0.0383
-4.750 0.2083 0.00950 0.00418 -0.1649 0.9336 0.0409
-4.500 0.2409 0.00902 0.00368 -0.1661 0.9296 0.0440
-4.250 0.2689 0.00878 0.00343 -0.1661 0.9234 0.0464
-4.000 0.2987 0.00854 0.00320 -0.1665 0.9169 0.0490
-3.750 0.3287 0.00836 0.00301 -0.1670 0.9086 0.0512
-3.500 0.3585 0.00821 0.00284 -0.1673 0.8960 0.0539
-3.250 0.3881 0.00809 0.00267 -0.1675 0.8793 0.0568
-3.000 0.4172 0.00803 0.00252 -0.1677 0.8577 0.0600
-2.750 0.4456 0.00801 0.00240 -0.1677 0.8348 0.0648
-2.500 0.4734 0.00801 0.00234 -0.1677 0.8133 0.0742
-2.250 0.5005 0.00804 0.00230 -0.1675 0.7929 0.0930
-2.000 0.5282 0.00805 0.00230 -0.1675 0.7773 0.1139
-1.750 0.5538 0.00812 0.00228 -0.1669 0.7327 0.1320
-1.500 0.5796 0.00825 0.00233 -0.1665 0.7121 0.1487
-1.250 0.6068 0.00833 0.00238 -0.1664 0.6970 0.1657
-1.000 0.6342 0.00841 0.00244 -0.1663 0.6802 0.1807
-0.750 0.6614 0.00850 0.00248 -0.1662 0.6629 0.1938
-0.500 0.6884 0.00860 0.00253 -0.1660 0.6455 0.2051
-0.250 0.7154 0.00869 0.00258 -0.1658 0.6276 0.2193
0.000 0.7425 0.00879 0.00264 -0.1657 0.6110 0.2325
0.250 0.7694 0.00889 0.00270 -0.1655 0.5911 0.2471
0.500 0.7957 0.00901 0.00277 -0.1653 0.5703 0.2698
0.750 0.8226 0.00904 0.00288 -0.1652 0.5531 0.3310
1.000 0.8498 0.00879 0.00309 -0.1656 0.5173 0.5710
1.250 0.8746 0.00871 0.00336 -0.1653 0.4777 0.7794
1.500 0.8871 0.00873 0.00358 -0.1616 0.4394 0.9383
1.750 0.9046 0.00897 0.00363 -0.1592 0.3950 1.0000
2.000 0.9287 0.00939 0.00383 -0.1586 0.3593 1.0000
2.250 0.9547 0.00964 0.00399 -0.1583 0.3482 1.0000
2.500 0.9814 0.00984 0.00413 -0.1581 0.3401 1.0000
2.750 1.0083 0.01002 0.00427 -0.1580 0.3330 1.0000
3.000 1.0345 0.01024 0.00444 -0.1577 0.3252 1.0000
3.250 1.0617 0.01037 0.00455 -0.1577 0.3178 1.0000
3.500 1.0878 0.01058 0.00471 -0.1574 0.3082 1.0000
3.750 1.1141 0.01076 0.00484 -0.1571 0.2967 1.0000
4.000 1.1396 0.01099 0.00500 -0.1568 0.2839 1.0000
4.250 1.1644 0.01126 0.00518 -0.1562 0.2696 1.0000
4.500 1.1888 0.01155 0.00539 -0.1556 0.2555 1.0000
4.750 1.2129 0.01183 0.00561 -0.1550 0.2421 1.0000
5.000 1.2370 0.01211 0.00582 -0.1544 0.2299 1.0000
5.250 1.2605 0.01241 0.00607 -0.1536 0.2175 1.0000
5.500 1.2831 0.01275 0.00634 -0.1526 0.2040 1.0000
5.750 1.3051 0.01312 0.00662 -0.1516 0.1900 1.0000
6.000 1.3267 0.01349 0.00693 -0.1504 0.1765 1.0000
6.250 1.3470 0.01391 0.00726 -0.1490 0.1618 1.0000
6.500 1.3651 0.01436 0.00764 -0.1472 0.1470 1.0000
6.750 1.3831 0.01484 0.00804 -0.1453 0.1330 1.0000
7.000 1.4004 0.01538 0.00850 -0.1434 0.1184 1.0000
7.250 1.4169 0.01596 0.00899 -0.1413 0.1021 1.0000
7.500 1.4334 0.01657 0.00952 -0.1392 0.0879 1.0000
7.750 1.4511 0.01710 0.01000 -0.1374 0.0793 1.0000
8.000 1.4695 0.01759 0.01047 -0.1358 0.0773 1.0000
8.250 1.4879 0.01808 0.01095 -0.1341 0.0754 1.0000
8.500 1.5064 0.01857 0.01145 -0.1326 0.0737 1.0000
8.750 1.5252 0.01902 0.01193 -0.1311 0.0726 1.0000
9.000 1.5440 0.01947 0.01243 -0.1296 0.0718 1.0000
9.250 1.5623 0.01995 0.01295 -0.1280 0.0708 1.0000
9.500 1.5800 0.02048 0.01352 -0.1264 0.0698 1.0000
9.750 1.5967 0.02107 0.01414 -0.1246 0.0689 1.0000
10.000 1.6123 0.02173 0.01483 -0.1227 0.0676 1.0000
10.250 1.6290 0.02232 0.01546 -0.1210 0.0665 1.0000
10.500 1.6480 0.02275 0.01593 -0.1198 0.0653 1.0000
10.750 1.6661 0.02324 0.01646 -0.1184 0.0637 1.0000
11.000 1.6832 0.02381 0.01706 -0.1169 0.0618 1.0000
11.250 1.6992 0.02444 0.01772 -0.1152 0.0602 1.0000
11.500 1.7152 0.02509 0.01839 -0.1136 0.0588 1.0000
11.750 1.7301 0.02581 0.01912 -0.1119 0.0569 1.0000
12.000 1.7433 0.02665 0.01998 -0.1099 0.0551 1.0000
12.250 1.7569 0.02746 0.02085 -0.1081 0.0536 1.0000
12.500 1.7682 0.02846 0.02187 -0.1060 0.0518 1.0000
12.750 1.7782 0.02955 0.02300 -0.1038 0.0499 1.0000
13.000 1.7946 0.03021 0.02373 -0.1025 0.0481 1.0000
13.250 1.8067 0.03118 0.02475 -0.1007 0.0453 1.0000
13.750 1.8267 0.03351 0.02703 -0.0968 0.0343 1.0000
14.000 1.8319 0.03511 0.02865 -0.0944 0.0324 1.0000
14.250 1.8388 0.03663 0.03025 -0.0924 0.0313 1.0000
14.500 1.8436 0.03837 0.03207 -0.0902 0.0303 1.0000
14.750 1.8461 0.04038 0.03415 -0.0880 0.0294 1.0000
15.000 1.8459 0.04271 0.03655 -0.0858 0.0283 1.0000
15.250 1.8525 0.04447 0.03840 -0.0843 0.0277 1.0000
15.500 1.8581 0.04637 0.04039 -0.0829 0.0269 1.0000
15.750 1.8607 0.04862 0.04273 -0.0814 0.0261 1.0000
16.000 1.8607 0.05125 0.04544 -0.0800 0.0252 1.0000
16.250 1.8580 0.05429 0.04856 -0.0786 0.0245 1.0000
16.500 1.8631 0.05651 0.05088 -0.0778 0.0238 1.0000
16.750 1.8657 0.05905 0.05351 -0.0770 0.0230 1.0000
17.000 1.8654 0.06200 0.05653 -0.0763 0.0222 1.0000
17.250 1.8622 0.06537 0.05999 -0.0757 0.0214 1.0000
17.500 1.8593 0.06877 0.06348 -0.0752 0.0207 1.0000
17.750 1.8577 0.07208 0.06688 -0.0750 0.0201 1.0000
18.000 1.8538 0.07569 0.07059 -0.0748 0.0194 1.0000
18.250 1.8475 0.07972 0.07471 -0.0748 0.0187 1.0000
18.500 1.8381 0.08426 0.07933 -0.0751 0.0181 1.0000
18.750 1.8290 0.08884 0.08403 -0.0755 0.0177 1.0000
19.000 1.8197 0.09356 0.08886 -0.0762 0.0172 1.0000
19.250 1.8089 0.09855 0.09396 -0.0772 0.0167 1.0000
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