HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 500,000 Max Cl/Cd: 103.4 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hs1712-il-500000.txt Download as CSV file: xf-hs1712-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3034 0.09624 0.09388 -0.0660 0.9836 0.0293
-9.000 -0.2870 0.09404 0.09168 -0.0673 0.9829 0.0295
-8.750 -0.4152 0.02948 0.02542 -0.1200 0.9646 0.0212
-8.500 -0.3855 0.02518 0.02035 -0.1234 0.9633 0.0220
-8.250 -0.3537 0.02359 0.01855 -0.1255 0.9622 0.0228
-8.000 -0.3199 0.02320 0.01813 -0.1272 0.9612 0.0236
-7.750 -0.2853 0.02221 0.01695 -0.1292 0.9605 0.0246
-7.500 -0.2498 0.02071 0.01509 -0.1314 0.9598 0.0256
-7.250 -0.2139 0.01989 0.01423 -0.1336 0.9592 0.0264
-7.000 -0.1769 0.01939 0.01365 -0.1358 0.9586 0.0275
-6.750 -0.1579 0.01888 0.01301 -0.1341 0.9523 0.0286
-6.500 -0.1241 0.01831 0.01235 -0.1355 0.9505 0.0299
-6.250 -0.0895 0.01792 0.01191 -0.1371 0.9491 0.0313
-6.000 -0.0539 0.01735 0.01115 -0.1388 0.9481 0.0331
-5.750 -0.0184 0.01675 0.01058 -0.1407 0.9472 0.0347
-5.500 0.0185 0.01634 0.01001 -0.1426 0.9465 0.0370
-5.250 0.0556 0.01553 0.00927 -0.1450 0.9459 0.0397
-5.000 0.0942 0.01472 0.00847 -0.1475 0.9454 0.0430
-4.750 0.1339 0.01398 0.00774 -0.1503 0.9450 0.0468
-4.500 0.1558 0.01372 0.00749 -0.1489 0.9387 0.0502
-4.250 0.1899 0.01336 0.00716 -0.1503 0.9363 0.0545
-4.000 0.2266 0.01297 0.00678 -0.1523 0.9350 0.0588
-3.750 0.2644 0.01256 0.00638 -0.1545 0.9340 0.0633
-3.500 0.3025 0.01218 0.00600 -0.1567 0.9328 0.0677
-3.250 0.3418 0.01170 0.00556 -0.1592 0.9314 0.0736
-3.000 0.3827 0.01116 0.00506 -0.1620 0.9296 0.0837
-2.750 0.4066 0.01083 0.00482 -0.1609 0.9205 0.1013
-2.500 0.4441 0.01031 0.00441 -0.1629 0.9156 0.1346
-2.250 0.4725 0.01005 0.00423 -0.1629 0.9069 0.1602
-2.000 0.5046 0.00980 0.00402 -0.1637 0.8994 0.1811
-1.750 0.5340 0.00964 0.00389 -0.1639 0.8898 0.1968
-1.500 0.5696 0.00940 0.00364 -0.1655 0.8809 0.2126
-1.250 0.6002 0.00926 0.00347 -0.1660 0.8662 0.2261
-1.000 0.6330 0.00911 0.00329 -0.1669 0.8489 0.2419
-0.750 0.6650 0.00902 0.00315 -0.1677 0.8289 0.2610
-0.500 0.6947 0.00897 0.00310 -0.1681 0.8066 0.2889
-0.250 0.7246 0.00887 0.00309 -0.1687 0.7874 0.3760
0.000 0.7518 0.00832 0.00328 -0.1690 0.7539 0.6470
0.250 0.7712 0.00811 0.00340 -0.1667 0.7281 0.8359
0.500 0.7803 0.00787 0.00322 -0.1618 0.7108 0.9997
0.750 0.8073 0.00809 0.00332 -0.1616 0.6941 1.0000
1.000 0.8344 0.00829 0.00341 -0.1614 0.6788 1.0000
1.250 0.8611 0.00848 0.00351 -0.1612 0.6631 1.0000
1.500 0.8873 0.00869 0.00360 -0.1608 0.6467 1.0000
1.750 0.9132 0.00888 0.00371 -0.1604 0.6295 1.0000
2.000 0.9387 0.00909 0.00382 -0.1599 0.6114 1.0000
2.250 0.9637 0.00932 0.00395 -0.1593 0.5901 1.0000
2.500 0.9876 0.00959 0.00410 -0.1585 0.5672 1.0000
2.750 1.0112 0.00988 0.00427 -0.1576 0.5401 1.0000
3.000 1.0319 0.01030 0.00447 -0.1561 0.4994 1.0000
3.250 1.0517 0.01080 0.00473 -0.1545 0.4565 1.0000
3.500 1.0721 0.01131 0.00503 -0.1531 0.4179 1.0000
3.750 1.0933 0.01178 0.00532 -0.1518 0.3856 1.0000
4.000 1.1154 0.01220 0.00559 -0.1508 0.3651 1.0000
4.250 1.1381 0.01257 0.00587 -0.1498 0.3534 1.0000
4.500 1.1605 0.01295 0.00618 -0.1488 0.3444 1.0000
4.750 1.1847 0.01321 0.00644 -0.1482 0.3368 1.0000
5.000 1.2074 0.01355 0.00674 -0.1472 0.3283 1.0000
5.250 1.2314 0.01379 0.00699 -0.1465 0.3200 1.0000
5.500 1.2540 0.01409 0.00726 -0.1456 0.3102 1.0000
5.750 1.2768 0.01433 0.00750 -0.1446 0.3001 1.0000
6.000 1.2977 0.01465 0.00779 -0.1433 0.2897 1.0000
6.250 1.3190 0.01497 0.00809 -0.1421 0.2791 1.0000
6.500 1.3399 0.01532 0.00841 -0.1408 0.2695 1.0000
6.750 1.3597 0.01573 0.00878 -0.1394 0.2587 1.0000
7.000 1.3805 0.01608 0.00914 -0.1381 0.2483 1.0000
7.250 1.4000 0.01652 0.00954 -0.1367 0.2381 1.0000
7.500 1.4197 0.01695 0.00995 -0.1353 0.2271 1.0000
7.750 1.4388 0.01741 0.01039 -0.1337 0.2161 1.0000
8.000 1.4569 0.01794 0.01088 -0.1321 0.2043 1.0000
8.250 1.4744 0.01850 0.01140 -0.1304 0.1909 1.0000
8.500 1.4915 0.01909 0.01195 -0.1286 0.1773 1.0000
8.750 1.5075 0.01975 0.01256 -0.1267 0.1631 1.0000
9.000 1.5226 0.02048 0.01323 -0.1246 0.1482 1.0000
9.250 1.5363 0.02130 0.01397 -0.1224 0.1330 1.0000
9.500 1.5500 0.02213 0.01475 -0.1202 0.1199 1.0000
9.750 1.5638 0.02296 0.01554 -0.1180 0.1092 1.0000
10.000 1.5773 0.02379 0.01636 -0.1159 0.1017 1.0000
10.250 1.5904 0.02467 0.01723 -0.1137 0.0961 1.0000
10.500 1.6050 0.02545 0.01805 -0.1118 0.0920 1.0000
10.750 1.6178 0.02636 0.01898 -0.1097 0.0887 1.0000
11.000 1.6316 0.02720 0.01987 -0.1078 0.0858 1.0000
11.250 1.6444 0.02811 0.02081 -0.1058 0.0828 1.0000
11.500 1.6557 0.02914 0.02187 -0.1037 0.0803 1.0000
11.750 1.6667 0.03021 0.02299 -0.1016 0.0784 1.0000
12.000 1.6765 0.03138 0.02421 -0.0994 0.0767 1.0000
12.250 1.6841 0.03274 0.02561 -0.0971 0.0751 1.0000
12.500 1.6885 0.03436 0.02726 -0.0944 0.0733 1.0000
12.750 1.6991 0.03555 0.02856 -0.0926 0.0718 1.0000
13.000 1.7080 0.03691 0.03001 -0.0908 0.0698 1.0000
13.250 1.7122 0.03870 0.03187 -0.0885 0.0679 1.0000
13.500 1.7183 0.04040 0.03365 -0.0866 0.0661 1.0000
13.750 1.7327 0.04141 0.03477 -0.0856 0.0634 1.0000
14.000 1.7417 0.04292 0.03635 -0.0842 0.0609 1.0000
14.250 1.7524 0.04429 0.03782 -0.0830 0.0585 1.0000
14.500 1.7593 0.04609 0.03963 -0.0816 0.0560 1.0000
14.750 1.7643 0.04810 0.04173 -0.0802 0.0536 1.0000
15.000 1.7654 0.05058 0.04427 -0.0788 0.0512 1.0000
15.250 1.7688 0.05291 0.04671 -0.0776 0.0488 1.0000
15.500 1.7746 0.05504 0.04894 -0.0767 0.0453 1.0000
15.750 1.7847 0.05672 0.05072 -0.0760 0.0399 1.0000
16.000 1.7873 0.05928 0.05326 -0.0753 0.0370 1.0000
16.250 1.7842 0.06259 0.05661 -0.0745 0.0351 1.0000
16.500 1.7767 0.06654 0.06064 -0.0738 0.0338 1.0000
16.750 1.7658 0.07105 0.06524 -0.0734 0.0327 1.0000
17.000 1.7542 0.07578 0.07008 -0.0732 0.0319 1.0000
17.250 1.7445 0.08037 0.07482 -0.0733 0.0310 1.0000
17.500 1.7324 0.08541 0.08001 -0.0737 0.0303 1.0000
17.750 1.7173 0.09103 0.08576 -0.0744 0.0297 1.0000
18.000 1.7003 0.09708 0.09194 -0.0756 0.0292 1.0000
18.250 1.6809 0.10364 0.09863 -0.0772 0.0287 1.0000
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