HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Reynolds number: 50,000 Max Cl/Cd: 30.54 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hh02-il-50000.txt Download as CSV file: xf-hh02-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HUGHES HELICOPTERS HH-02 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5049 0.09640 0.09105 0.0249 1.0000 0.3138
-7.250 -0.4937 0.09278 0.08745 0.0242 1.0000 0.3320
-7.000 -0.4976 0.09045 0.08519 0.0219 1.0000 0.3533
-6.750 -0.4750 0.08586 0.08059 0.0227 1.0000 0.3735
-6.500 -0.4731 0.08334 0.07813 0.0220 1.0000 0.4008
-6.250 -0.4616 0.08031 0.07511 0.0227 1.0000 0.4309
-6.000 -0.4332 0.07583 0.07059 0.0236 1.0000 0.4553
-5.750 -0.4644 0.05980 0.05420 -0.0210 1.0000 0.2356
-5.500 -0.4551 0.04862 0.04193 -0.0312 1.0000 0.1505
-5.250 -0.4456 0.04437 0.03692 -0.0313 1.0000 0.1394
-5.000 -0.4327 0.04126 0.03352 -0.0303 1.0000 0.1378
-4.750 -0.4177 0.03825 0.03011 -0.0293 1.0000 0.1353
-4.500 -0.4000 0.03536 0.02671 -0.0283 1.0000 0.1324
-4.250 -0.3803 0.03291 0.02379 -0.0273 1.0000 0.1321
-4.000 -0.3596 0.03105 0.02149 -0.0264 1.0000 0.1371
-3.750 -0.3370 0.02927 0.01921 -0.0255 1.0000 0.1417
-3.500 -0.3138 0.02750 0.01737 -0.0248 1.0000 0.1475
-3.250 -0.2900 0.02613 0.01581 -0.0242 1.0000 0.1591
-3.000 -0.2650 0.02484 0.01447 -0.0236 1.0000 0.1744
-2.750 -0.2393 0.02366 0.01327 -0.0232 1.0000 0.2003
-2.500 -0.2103 0.02200 0.01203 -0.0235 1.0000 0.2637
-2.250 -0.2028 0.01937 0.01194 -0.0167 1.0000 0.7257
-2.000 -0.1441 0.01870 0.01146 -0.0205 1.0000 1.0000
-1.750 -0.1263 0.01887 0.01118 -0.0203 1.0000 1.0000
-1.500 -0.1069 0.01912 0.01104 -0.0203 1.0000 1.0000
-1.250 -0.0868 0.01942 0.01101 -0.0203 1.0000 1.0000
-1.000 -0.0665 0.01978 0.01106 -0.0203 1.0000 1.0000
-0.750 -0.0460 0.02018 0.01119 -0.0203 1.0000 1.0000
-0.500 -0.0256 0.02063 0.01137 -0.0203 1.0000 1.0000
-0.250 -0.0053 0.02111 0.01165 -0.0203 1.0000 1.0000
0.000 0.0357 0.02188 0.01218 -0.0243 0.9926 1.0000
0.250 0.0847 0.02282 0.01290 -0.0296 0.9819 1.0000
0.500 0.1326 0.02381 0.01373 -0.0347 0.9698 1.0000
0.750 0.1788 0.02486 0.01465 -0.0394 0.9562 1.0000
1.000 0.2263 0.02603 0.01573 -0.0441 0.9412 1.0000
1.250 0.2726 0.02729 0.01694 -0.0484 0.9248 1.0000
1.500 0.3088 0.02850 0.01813 -0.0508 0.9068 1.0000
1.750 0.3467 0.02977 0.01940 -0.0532 0.8879 1.0000
2.000 0.3816 0.03094 0.02060 -0.0549 0.8686 1.0000
2.250 0.4143 0.03198 0.02168 -0.0559 0.8489 1.0000
2.500 0.4420 0.03290 0.02263 -0.0560 0.8285 1.0000
2.750 0.4731 0.03371 0.02351 -0.0562 0.8076 1.0000
3.000 0.5041 0.03442 0.02430 -0.0558 0.7867 1.0000
3.250 0.5293 0.03499 0.02495 -0.0547 0.7640 1.0000
3.500 0.5594 0.03529 0.02533 -0.0534 0.7434 1.0000
3.750 0.5820 0.03561 0.02574 -0.0516 0.7192 1.0000
4.000 0.6116 0.03526 0.02552 -0.0489 0.6998 1.0000
4.250 0.6332 0.03531 0.02566 -0.0466 0.6745 1.0000
4.500 0.6602 0.03438 0.02483 -0.0428 0.6559 1.0000
4.750 0.6825 0.03403 0.02459 -0.0400 0.6310 1.0000
5.000 0.7080 0.03273 0.02340 -0.0355 0.6123 1.0000
5.250 0.7310 0.03203 0.02280 -0.0322 0.5881 1.0000
5.500 0.7552 0.03062 0.02143 -0.0275 0.5677 1.0000
5.750 0.7782 0.02989 0.02077 -0.0240 0.5415 1.0000
6.000 0.8013 0.02904 0.01991 -0.0201 0.5158 1.0000
6.250 0.8242 0.02838 0.01918 -0.0165 0.4884 1.0000
6.500 0.8473 0.02831 0.01904 -0.0138 0.4579 1.0000
6.750 0.8704 0.02863 0.01931 -0.0118 0.4263 1.0000
7.000 0.8935 0.02926 0.01984 -0.0101 0.3954 1.0000
7.250 0.9166 0.03020 0.02069 -0.0087 0.3658 1.0000
7.500 0.9394 0.03137 0.02176 -0.0074 0.3371 1.0000
7.750 0.9624 0.03265 0.02288 -0.0061 0.3108 1.0000
8.000 0.9843 0.03447 0.02486 -0.0057 0.2843 1.0000
8.250 1.0057 0.03637 0.02683 -0.0052 0.2607 1.0000
8.500 1.0270 0.03846 0.02903 -0.0046 0.2403 1.0000
8.750 1.0490 0.04030 0.03075 -0.0036 0.2213 1.0000
9.000 1.0669 0.04298 0.03377 -0.0034 0.2048 1.0000
9.250 1.0837 0.04566 0.03667 -0.0030 0.1897 1.0000
9.500 1.1015 0.04836 0.03948 -0.0024 0.1768 1.0000
9.750 1.1062 0.05258 0.04433 -0.0026 0.1676 1.0000
10.000 1.1118 0.05641 0.04844 -0.0024 0.1587 1.0000
10.250 1.1095 0.06102 0.05344 -0.0025 0.1533 1.0000
10.500 1.1144 0.06500 0.05754 -0.0020 0.1470 1.0000
10.750 1.0921 0.07108 0.06398 -0.0032 0.1466 1.0000
11.000 1.0657 0.07728 0.07036 -0.0048 0.1474 1.0000
11.250 1.0396 0.08388 0.07704 -0.0067 0.1483 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)