HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Reynolds number: 100,000 Max Cl/Cd: 46.5 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hh02-il-100000.txt Download as CSV file: xf-hh02-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5692 0.11466 0.11077 0.0264 1.0000 0.0912
-9.000 -0.5728 0.11062 0.10678 0.0193 1.0000 0.0955
-8.750 -0.5891 0.10595 0.10219 0.0047 1.0000 0.0967
-8.500 -0.5569 0.10119 0.09740 0.0149 1.0000 0.1005
-8.250 -0.5462 0.09747 0.09368 0.0128 1.0000 0.1059
-8.000 -0.5572 0.09193 0.08819 -0.0023 1.0000 0.1107
-7.750 -0.5392 0.08789 0.08418 0.0020 1.0000 0.1153
-7.500 -0.5305 0.08368 0.07997 -0.0040 1.0000 0.1234
-7.250 -0.5238 0.07775 0.07403 -0.0115 1.0000 0.1291
-6.750 -0.4989 0.06884 0.06503 -0.0198 1.0000 0.1455
-6.500 -0.4924 0.06381 0.05984 -0.0267 1.0000 0.1580
-6.250 -0.4766 0.06130 0.05738 -0.0252 1.0000 0.1656
-6.000 -0.4762 0.05804 0.05405 -0.0259 1.0000 0.1757
-5.750 -0.4591 0.05451 0.05043 -0.0282 0.9950 0.1912
-5.500 -0.4204 0.03744 0.03100 -0.0398 0.9862 0.0815
-5.250 -0.3866 0.03314 0.02629 -0.0422 0.9811 0.0798
-5.000 -0.3542 0.02957 0.02222 -0.0436 0.9751 0.0771
-4.750 -0.3174 0.02656 0.01862 -0.0453 0.9700 0.0755
-4.500 -0.2850 0.02481 0.01646 -0.0460 0.9639 0.0788
-4.250 -0.2513 0.02355 0.01473 -0.0467 0.9577 0.0823
-4.000 -0.2204 0.02170 0.01287 -0.0473 0.9520 0.0863
-3.750 -0.1917 0.02097 0.01204 -0.0474 0.9451 0.0951
-3.500 -0.1635 0.02003 0.01120 -0.0474 0.9389 0.1042
-3.250 -0.1390 0.01937 0.01061 -0.0468 0.9316 0.1189
-3.000 -0.1149 0.01886 0.01024 -0.0460 0.9250 0.1466
-2.750 -0.0999 0.01671 0.00999 -0.0443 0.9176 0.4905
-2.500 -0.0827 0.01702 0.01061 -0.0413 0.9101 0.6407
-2.250 -0.0622 0.01732 0.01092 -0.0392 0.9028 0.7017
-2.000 -0.0402 0.01726 0.01095 -0.0376 0.8950 0.7562
-1.750 0.0249 0.01687 0.01108 -0.0422 0.8909 0.8912
-1.500 0.0816 0.01714 0.01113 -0.0482 0.8844 0.9953
-1.250 0.1087 0.01747 0.01125 -0.0493 0.8757 1.0000
-1.000 0.1317 0.01787 0.01146 -0.0492 0.8670 1.0000
-0.750 0.1540 0.01831 0.01173 -0.0485 0.8586 1.0000
-0.500 0.1779 0.01865 0.01192 -0.0481 0.8491 1.0000
-0.250 0.2015 0.01896 0.01211 -0.0476 0.8387 1.0000
0.000 0.2234 0.01927 0.01230 -0.0462 0.8283 1.0000
0.250 0.2433 0.01954 0.01244 -0.0439 0.8188 1.0000
0.500 0.2676 0.01975 0.01257 -0.0433 0.8072 1.0000
0.750 0.2908 0.01998 0.01273 -0.0422 0.7968 1.0000
1.000 0.3102 0.02011 0.01278 -0.0395 0.7891 1.0000
1.250 0.3355 0.02030 0.01292 -0.0391 0.7775 1.0000
1.500 0.3593 0.02045 0.01304 -0.0381 0.7668 1.0000
1.750 0.3783 0.02035 0.01288 -0.0349 0.7597 1.0000
2.000 0.4033 0.02043 0.01296 -0.0342 0.7474 1.0000
2.250 0.4269 0.02043 0.01295 -0.0329 0.7360 1.0000
2.500 0.4452 0.02004 0.01251 -0.0291 0.7295 1.0000
2.750 0.4694 0.01993 0.01241 -0.0279 0.7166 1.0000
3.000 0.4926 0.01971 0.01223 -0.0261 0.7042 1.0000
3.250 0.5149 0.01937 0.01189 -0.0239 0.6924 1.0000
3.500 0.5354 0.01883 0.01133 -0.0208 0.6822 1.0000
3.750 0.5563 0.01826 0.01075 -0.0178 0.6708 1.0000
4.000 0.5789 0.01779 0.01032 -0.0155 0.6565 1.0000
4.250 0.6013 0.01730 0.00983 -0.0130 0.6413 1.0000
4.500 0.6248 0.01690 0.00944 -0.0110 0.6229 1.0000
4.750 0.6489 0.01656 0.00910 -0.0093 0.6010 1.0000
5.000 0.6724 0.01624 0.00876 -0.0073 0.5772 1.0000
5.250 0.6972 0.01607 0.00854 -0.0058 0.5480 1.0000
5.500 0.7232 0.01609 0.00849 -0.0049 0.5122 1.0000
5.750 0.7488 0.01626 0.00850 -0.0040 0.4756 1.0000
6.000 0.7757 0.01668 0.00878 -0.0039 0.4347 1.0000
6.250 0.8020 0.01727 0.00917 -0.0037 0.3976 1.0000
6.500 0.8282 0.01802 0.00974 -0.0037 0.3628 1.0000
6.750 0.8540 0.01886 0.01045 -0.0038 0.3313 1.0000
7.000 0.8796 0.01977 0.01124 -0.0039 0.3024 1.0000
7.250 0.9048 0.02069 0.01207 -0.0040 0.2756 1.0000
7.500 0.9295 0.02165 0.01289 -0.0040 0.2515 1.0000
7.750 0.9544 0.02263 0.01395 -0.0041 0.2276 1.0000
8.000 0.9781 0.02370 0.01489 -0.0040 0.2071 1.0000
8.250 1.0018 0.02481 0.01608 -0.0041 0.1858 1.0000
8.500 1.0245 0.02597 0.01723 -0.0040 0.1672 1.0000
8.750 1.0465 0.02725 0.01847 -0.0037 0.1508 1.0000
9.000 1.0682 0.02866 0.01990 -0.0034 0.1365 1.0000
9.250 1.0891 0.03011 0.02143 -0.0031 0.1232 1.0000
9.500 1.1093 0.03177 0.02324 -0.0026 0.1117 1.0000
9.750 1.1285 0.03355 0.02514 -0.0021 0.1013 1.0000
10.000 1.1475 0.03545 0.02700 -0.0016 0.0921 1.0000
10.250 1.1643 0.03714 0.02893 -0.0011 0.0835 1.0000
10.500 1.1787 0.03967 0.03172 -0.0005 0.0762 1.0000
10.750 1.1948 0.04165 0.03364 0.0001 0.0693 1.0000
11.000 1.2013 0.04472 0.03722 0.0009 0.0644 1.0000
11.250 1.2100 0.04693 0.03962 0.0015 0.0597 1.0000
11.500 1.2182 0.05090 0.04364 0.0022 0.0563 1.0000
11.750 1.2096 0.05431 0.04757 0.0028 0.0548 1.0000
12.000 1.1953 0.05783 0.05144 0.0039 0.0536 1.0000
12.250 1.1790 0.06180 0.05571 0.0043 0.0527 1.0000
12.500 1.1602 0.06637 0.06056 0.0039 0.0523 1.0000
12.750 1.1375 0.07182 0.06628 0.0024 0.0523 1.0000
13.000 1.1110 0.07837 0.07308 -0.0004 0.0530 1.0000
13.250 1.0829 0.08592 0.08083 -0.0043 0.0539 1.0000
13.500 1.0553 0.09429 0.08934 -0.0091 0.0550 1.0000
13.750 1.0294 0.10325 0.09840 -0.0143 0.0560 1.0000
14.000 0.8940 0.15009 0.14514 -0.0436 0.0799 1.0000
14.250 0.8945 0.15622 0.15127 -0.0453 0.0805 1.0000
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Polar data table (+)
Polar graphs
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