HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il) Reynolds number: 500,000 Max Cl/Cd: 83.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hs1712-il-500000-n5.txt Download as CSV file: xf-hs1712-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6476 0.03443 0.03078 -0.1267 0.9722 0.0126
-11.500 -0.6272 0.03032 0.02628 -0.1308 0.9715 0.0128
-11.250 -0.6135 0.02813 0.02381 -0.1306 0.9680 0.0130
-11.000 -0.5919 0.02628 0.02172 -0.1315 0.9659 0.0133
-10.750 -0.5663 0.02487 0.02018 -0.1327 0.9645 0.0135
-10.500 -0.5383 0.02374 0.01894 -0.1340 0.9633 0.0138
-10.250 -0.5090 0.02272 0.01778 -0.1353 0.9624 0.0142
-10.000 -0.4784 0.02173 0.01666 -0.1368 0.9615 0.0146
-9.750 -0.4458 0.02076 0.01554 -0.1387 0.9607 0.0151
-9.500 -0.4115 0.01982 0.01442 -0.1408 0.9599 0.0157
-9.250 -0.3765 0.01888 0.01334 -0.1430 0.9593 0.0162
-9.000 -0.3418 0.01810 0.01249 -0.1451 0.9587 0.0167
-8.750 -0.3224 0.01764 0.01196 -0.1435 0.9540 0.0172
-8.500 -0.2939 0.01706 0.01129 -0.1441 0.9519 0.0178
-8.250 -0.2633 0.01647 0.01059 -0.1450 0.9505 0.0184
-8.000 -0.2316 0.01592 0.00992 -0.1461 0.9494 0.0190
-7.750 -0.1994 0.01534 0.00932 -0.1474 0.9484 0.0198
-7.500 -0.1663 0.01488 0.00880 -0.1488 0.9473 0.0208
-7.250 -0.1325 0.01440 0.00824 -0.1503 0.9462 0.0219
-7.000 -0.0984 0.01393 0.00773 -0.1519 0.9452 0.0230
-6.750 -0.0646 0.01356 0.00734 -0.1533 0.9442 0.0241
-6.500 -0.0432 0.01335 0.00709 -0.1519 0.9390 0.0252
-6.250 -0.0142 0.01311 0.00685 -0.1522 0.9362 0.0265
-6.000 0.0172 0.01290 0.00663 -0.1531 0.9341 0.0281
-5.750 0.0496 0.01269 0.00639 -0.1541 0.9323 0.0301
-5.500 0.0827 0.01247 0.00611 -0.1552 0.9306 0.0326
-5.250 0.1171 0.01218 0.00580 -0.1567 0.9290 0.0347
-5.000 0.1396 0.01209 0.00565 -0.1554 0.9221 0.0368
-4.750 0.1706 0.01171 0.00527 -0.1562 0.9175 0.0390
-4.500 0.2047 0.01142 0.00492 -0.1576 0.9144 0.0412
-4.250 0.2326 0.01110 0.00462 -0.1578 0.9087 0.0432
-4.000 0.2614 0.01088 0.00438 -0.1580 0.9024 0.0452
-3.750 0.2948 0.01060 0.00411 -0.1592 0.8979 0.0475
-3.500 0.3240 0.01042 0.00394 -0.1595 0.8899 0.0496
-3.250 0.3591 0.01017 0.00368 -0.1611 0.8806 0.0537
-3.000 0.3921 0.00997 0.00342 -0.1621 0.8630 0.0600
-2.750 0.4259 0.00981 0.00315 -0.1633 0.8355 0.0665
-2.500 0.4557 0.00978 0.00299 -0.1636 0.8028 0.0764
-2.250 0.4840 0.00983 0.00292 -0.1636 0.7819 0.0909
-2.000 0.5103 0.00986 0.00288 -0.1632 0.7401 0.1052
-1.750 0.5352 0.01000 0.00287 -0.1626 0.7170 0.1190
-1.500 0.5618 0.01011 0.00290 -0.1623 0.7007 0.1337
-1.250 0.5888 0.01019 0.00295 -0.1621 0.6828 0.1480
-1.000 0.6156 0.01028 0.00300 -0.1619 0.6650 0.1634
-0.750 0.6420 0.01038 0.00305 -0.1616 0.6462 0.1785
-0.500 0.6684 0.01049 0.00311 -0.1613 0.6286 0.1913
-0.250 0.6949 0.01060 0.00316 -0.1610 0.6112 0.2033
0.000 0.7210 0.01071 0.00323 -0.1607 0.5907 0.2169
0.250 0.7463 0.01087 0.00331 -0.1602 0.5694 0.2298
0.500 0.7722 0.01099 0.00340 -0.1599 0.5514 0.2485
0.750 0.7964 0.01118 0.00352 -0.1592 0.5145 0.2776
1.000 0.8199 0.01136 0.00370 -0.1585 0.4758 0.3509
1.250 0.8448 0.01104 0.00406 -0.1586 0.4361 0.6825
1.500 0.8634 0.01110 0.00437 -0.1565 0.3958 0.8377
1.750 0.8721 0.01108 0.00440 -0.1518 0.3679 0.9843
2.000 0.8966 0.01133 0.00452 -0.1512 0.3533 1.0000
2.250 0.9220 0.01160 0.00470 -0.1508 0.3444 1.0000
2.500 0.9482 0.01181 0.00486 -0.1505 0.3377 1.0000
2.750 0.9740 0.01203 0.00504 -0.1502 0.3302 1.0000
3.000 0.9997 0.01226 0.00522 -0.1498 0.3230 1.0000
3.250 1.0255 0.01246 0.00539 -0.1495 0.3133 1.0000
3.500 1.0509 0.01269 0.00557 -0.1491 0.3039 1.0000
3.750 1.0756 0.01295 0.00577 -0.1485 0.2916 1.0000
4.000 1.1003 0.01320 0.00597 -0.1480 0.2804 1.0000
4.250 1.1245 0.01347 0.00618 -0.1474 0.2704 1.0000
4.500 1.1484 0.01375 0.00641 -0.1467 0.2604 1.0000
4.750 1.1720 0.01403 0.00665 -0.1459 0.2507 1.0000
5.000 1.1946 0.01436 0.00692 -0.1450 0.2389 1.0000
5.250 1.2163 0.01472 0.00721 -0.1439 0.2251 1.0000
5.500 1.2366 0.01509 0.00753 -0.1425 0.2113 1.0000
5.750 1.2564 0.01550 0.00787 -0.1410 0.1979 1.0000
6.000 1.2760 0.01594 0.00824 -0.1395 0.1847 1.0000
6.250 1.2955 0.01639 0.00864 -0.1380 0.1729 1.0000
6.500 1.3148 0.01685 0.00905 -0.1364 0.1607 1.0000
6.750 1.3344 0.01730 0.00947 -0.1350 0.1504 1.0000
7.000 1.3528 0.01783 0.00994 -0.1334 0.1379 1.0000
7.250 1.3709 0.01838 0.01044 -0.1317 0.1265 1.0000
7.500 1.3890 0.01893 0.01094 -0.1301 0.1161 1.0000
7.750 1.4066 0.01951 0.01149 -0.1284 0.1053 1.0000
8.000 1.4238 0.02012 0.01206 -0.1266 0.0965 1.0000
8.250 1.4405 0.02075 0.01266 -0.1248 0.0860 1.0000
8.500 1.4572 0.02139 0.01328 -0.1231 0.0791 1.0000
8.750 1.4738 0.02203 0.01391 -0.1213 0.0769 1.0000
9.000 1.4905 0.02266 0.01456 -0.1196 0.0752 1.0000
9.250 1.5072 0.02330 0.01522 -0.1179 0.0737 1.0000
9.500 1.5241 0.02392 0.01588 -0.1163 0.0725 1.0000
9.750 1.5408 0.02454 0.01657 -0.1147 0.0715 1.0000
10.000 1.5570 0.02521 0.01730 -0.1130 0.0704 1.0000
10.250 1.5721 0.02595 0.01809 -0.1112 0.0692 1.0000
10.500 1.5860 0.02679 0.01898 -0.1093 0.0680 1.0000
10.750 1.5992 0.02768 0.01992 -0.1073 0.0670 1.0000
11.000 1.6146 0.02840 0.02072 -0.1057 0.0658 1.0000
11.250 1.6304 0.02910 0.02150 -0.1042 0.0640 1.0000
11.500 1.6448 0.02993 0.02240 -0.1025 0.0618 1.0000
11.750 1.6578 0.03086 0.02338 -0.1007 0.0599 1.0000
12.000 1.6705 0.03183 0.02440 -0.0990 0.0582 1.0000
12.250 1.6820 0.03290 0.02551 -0.0971 0.0566 1.0000
12.500 1.6925 0.03406 0.02671 -0.0953 0.0550 1.0000
12.750 1.7026 0.03527 0.02799 -0.0934 0.0534 1.0000
13.000 1.7110 0.03667 0.02944 -0.0915 0.0515 1.0000
13.250 1.7181 0.03820 0.03103 -0.0895 0.0499 1.0000
13.500 1.7303 0.03935 0.03230 -0.0881 0.0477 1.0000
13.750 1.7403 0.04070 0.03374 -0.0866 0.0445 1.0000
14.000 1.7481 0.04229 0.03532 -0.0851 0.0357 1.0000
14.250 1.7517 0.04431 0.03735 -0.0833 0.0337 1.0000
14.500 1.7537 0.04656 0.03964 -0.0816 0.0319 1.0000
14.750 1.7564 0.04883 0.04201 -0.0800 0.0308 1.0000
15.000 1.7566 0.05143 0.04470 -0.0785 0.0296 1.0000
15.250 1.7551 0.05433 0.04770 -0.0772 0.0287 1.0000
15.500 1.7552 0.05714 0.05062 -0.0761 0.0278 1.0000
15.750 1.7564 0.05990 0.05349 -0.0753 0.0270 1.0000
16.000 1.7554 0.06299 0.05670 -0.0746 0.0261 1.0000
16.250 1.7522 0.06643 0.06025 -0.0740 0.0253 1.0000
16.500 1.7467 0.07025 0.06418 -0.0736 0.0246 1.0000
16.750 1.7445 0.07370 0.06776 -0.0734 0.0240 1.0000
17.000 1.7414 0.07733 0.07151 -0.0734 0.0233 1.0000
17.250 1.7363 0.08133 0.07563 -0.0735 0.0225 1.0000
17.500 1.7292 0.08568 0.08010 -0.0739 0.0219 1.0000
17.750 1.7199 0.09044 0.08498 -0.0745 0.0213 1.0000
18.000 1.7104 0.09534 0.09000 -0.0754 0.0209 1.0000
18.250 1.7023 0.10008 0.09488 -0.0764 0.0203 1.0000
18.500 1.6926 0.10517 0.10010 -0.0777 0.0198 1.0000
18.750 1.6820 0.11050 0.10556 -0.0793 0.0193 1.0000
19.000 1.6705 0.11607 0.11125 -0.0812 0.0189 1.0000
19.250 1.6589 0.12173 0.11703 -0.0833 0.0184 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HAM-STD HS1-712 AIRFOIL (hs1712-il)