HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Reynolds number: 200,000 Max Cl/Cd: 60.92 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hh02-il-200000.txt Download as CSV file: xf-hh02-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4696 0.10391 0.10120 0.0165 0.9156 0.0481
-9.000 -0.4698 0.10003 0.09732 0.0153 0.9123 0.0494
-8.750 -0.6078 0.10138 0.09863 0.0214 0.9243 0.0447
-8.500 -0.5973 0.09905 0.09629 0.0227 0.9202 0.0461
-8.250 -0.5932 0.09560 0.09284 0.0212 0.9157 0.0473
-8.000 -0.5904 0.09155 0.08879 0.0182 0.9112 0.0486
-7.750 -0.5891 0.08687 0.08413 0.0136 0.9060 0.0499
-7.500 -0.5880 0.08153 0.07877 0.0073 0.9012 0.0513
-7.250 -0.5837 0.07123 0.06812 -0.0102 0.8956 0.0547
-7.000 -0.5785 0.06725 0.06363 -0.0143 0.8909 0.0554
-6.750 -0.5707 0.05928 0.05585 -0.0157 0.8867 0.0572
-6.500 -0.5567 0.05679 0.05336 -0.0152 0.8824 0.0588
-6.250 -0.5380 0.05345 0.04990 -0.0167 0.8775 0.0618
-6.000 -0.5249 0.04853 0.04416 -0.0189 0.8728 0.0698
-5.750 -0.5044 0.04510 0.04087 -0.0193 0.8683 0.0721
-5.500 -0.4830 0.04269 0.03833 -0.0195 0.8635 0.0764
-5.250 -0.4656 0.03984 0.03512 -0.0192 0.8594 0.0863
-5.000 -0.4407 0.03763 0.03269 -0.0201 0.8540 0.1000
-4.750 -0.4073 0.02694 0.02009 -0.0166 0.8506 0.0424
-4.500 -0.3846 0.02542 0.01822 -0.0149 0.8470 0.0429
-4.250 -0.3551 0.02273 0.01532 -0.0157 0.8414 0.0459
-4.000 -0.3292 0.02152 0.01399 -0.0151 0.8367 0.0480
-3.750 -0.3061 0.02055 0.01289 -0.0135 0.8333 0.0502
-3.500 -0.2750 0.01973 0.01196 -0.0141 0.8274 0.0541
-3.250 -0.2498 0.01854 0.01075 -0.0133 0.8227 0.0584
-3.000 -0.2269 0.01784 0.01004 -0.0119 0.8193 0.0635
-2.750 -0.1977 0.01711 0.00931 -0.0123 0.8135 0.0722
-2.500 -0.1712 0.01649 0.00870 -0.0118 0.8086 0.0854
-2.250 -0.1479 0.01566 0.00810 -0.0105 0.8052 0.1304
-2.000 -0.1254 0.01389 0.00793 -0.0103 0.7999 0.4994
-1.750 -0.1001 0.01369 0.00796 -0.0095 0.7945 0.5958
-1.500 -0.0770 0.01357 0.00786 -0.0078 0.7910 0.6447
-1.250 -0.0504 0.01347 0.00780 -0.0072 0.7858 0.6808
-1.000 -0.0241 0.01329 0.00766 -0.0066 0.7800 0.7178
-0.750 -0.0028 0.01280 0.00735 -0.0045 0.7763 0.7661
-0.500 0.0279 0.01225 0.00726 -0.0041 0.7706 0.8513
-0.250 0.0843 0.01202 0.00697 -0.0094 0.7638 1.0000
0.000 0.1043 0.01178 0.00656 -0.0070 0.7594 1.0000
0.250 0.1339 0.01175 0.00645 -0.0074 0.7498 1.0000
0.500 0.1567 0.01159 0.00615 -0.0058 0.7455 1.0000
0.750 0.1861 0.01161 0.00611 -0.0061 0.7371 1.0000
1.000 0.2104 0.01148 0.00587 -0.0049 0.7318 1.0000
1.250 0.2378 0.01144 0.00578 -0.0046 0.7245 1.0000
1.500 0.2634 0.01133 0.00559 -0.0037 0.7178 1.0000
1.750 0.2899 0.01125 0.00545 -0.0030 0.7106 1.0000
2.000 0.3160 0.01113 0.00528 -0.0023 0.7028 1.0000
2.250 0.3429 0.01105 0.00517 -0.0018 0.6943 1.0000
2.500 0.3682 0.01090 0.00495 -0.0007 0.6863 1.0000
2.750 0.3960 0.01083 0.00487 -0.0004 0.6754 1.0000
3.000 0.4226 0.01073 0.00473 0.0002 0.6647 1.0000
3.250 0.4486 0.01062 0.00458 0.0011 0.6539 1.0000
3.500 0.4757 0.01055 0.00448 0.0016 0.6408 1.0000
3.750 0.5034 0.01053 0.00443 0.0019 0.6261 1.0000
4.000 0.5311 0.01052 0.00441 0.0022 0.6099 1.0000
4.250 0.5597 0.01055 0.00445 0.0022 0.5897 1.0000
4.500 0.5877 0.01060 0.00445 0.0024 0.5678 1.0000
4.750 0.6164 0.01070 0.00450 0.0023 0.5406 1.0000
5.000 0.6452 0.01087 0.00460 0.0022 0.5083 1.0000
5.250 0.6746 0.01114 0.00475 0.0018 0.4678 1.0000
5.500 0.7042 0.01156 0.00498 0.0011 0.4230 1.0000
5.750 0.7338 0.01210 0.00534 0.0002 0.3808 1.0000
6.000 0.7631 0.01272 0.00578 -0.0006 0.3446 1.0000
6.250 0.7919 0.01334 0.00626 -0.0015 0.3136 1.0000
6.500 0.8205 0.01394 0.00677 -0.0022 0.2853 1.0000
6.750 0.8486 0.01455 0.00732 -0.0029 0.2603 1.0000
7.000 0.8763 0.01518 0.00788 -0.0035 0.2377 1.0000
7.250 0.9038 0.01579 0.00848 -0.0041 0.2159 1.0000
7.500 0.9307 0.01647 0.00909 -0.0047 0.1944 1.0000
7.750 0.9570 0.01719 0.00978 -0.0052 0.1742 1.0000
8.000 0.9828 0.01793 0.01051 -0.0056 0.1551 1.0000
8.250 1.0077 0.01879 0.01133 -0.0060 0.1379 1.0000
8.500 1.0316 0.01975 0.01223 -0.0064 0.1221 1.0000
8.750 1.0547 0.02073 0.01322 -0.0065 0.1081 1.0000
9.000 1.0775 0.02168 0.01419 -0.0066 0.0959 1.0000
9.250 1.0994 0.02269 0.01526 -0.0066 0.0854 1.0000
9.500 1.1196 0.02389 0.01650 -0.0065 0.0762 1.0000
9.750 1.1375 0.02533 0.01788 -0.0064 0.0680 1.0000
10.000 1.1579 0.02625 0.01898 -0.0064 0.0604 1.0000
10.250 1.1736 0.02780 0.02058 -0.0061 0.0539 1.0000
10.500 1.1892 0.02909 0.02193 -0.0060 0.0479 1.0000
10.750 1.2012 0.03087 0.02382 -0.0053 0.0428 1.0000
11.000 1.2112 0.03231 0.02533 -0.0046 0.0385 1.0000
11.250 1.2164 0.03465 0.02770 -0.0031 0.0352 1.0000
11.500 1.2241 0.03631 0.02957 -0.0022 0.0322 1.0000
11.750 1.2303 0.03806 0.03140 -0.0015 0.0297 1.0000
12.000 1.2326 0.04095 0.03430 -0.0003 0.0275 1.0000
12.250 1.2371 0.04314 0.03675 0.0004 0.0262 1.0000
12.500 1.2398 0.04571 0.03953 0.0010 0.0250 1.0000
12.750 1.2410 0.04846 0.04246 0.0014 0.0241 1.0000
13.000 1.2411 0.05133 0.04548 0.0016 0.0232 1.0000
13.250 1.2398 0.05442 0.04870 0.0016 0.0226 1.0000
13.500 1.2367 0.05786 0.05226 0.0014 0.0221 1.0000
13.750 1.2303 0.06189 0.05646 0.0010 0.0217 1.0000
14.000 1.2197 0.06666 0.06143 0.0001 0.0214 1.0000
14.250 1.2052 0.07206 0.06706 -0.0015 0.0213 1.0000
14.500 1.1888 0.07794 0.07315 -0.0038 0.0212 1.0000
14.750 1.1719 0.08419 0.07962 -0.0069 0.0212 1.0000
15.000 1.1545 0.09100 0.08664 -0.0106 0.0212 1.0000
15.250 1.1366 0.09842 0.09426 -0.0151 0.0213 1.0000
15.500 1.1168 0.10684 0.10289 -0.0206 0.0215 1.0000
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Polar data table (+)
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