HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Reynolds number: 50,000 Max Cl/Cd: 33.43 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hh02-il-50000-n5.txt Download as CSV file: xf-hh02-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5998 0.14210 0.13633 0.0401 1.0000 0.1067
-10.500 -0.6062 0.13939 0.13368 0.0347 1.0000 0.1106
-10.250 -0.6122 0.13622 0.13057 0.0292 1.0000 0.1113
-10.000 -0.5967 0.13039 0.12476 0.0292 1.0000 0.1124
-9.750 -0.5844 0.12558 0.11993 0.0282 1.0000 0.1135
-9.500 -0.5768 0.12114 0.11551 0.0260 1.0000 0.1142
-9.250 -0.5687 0.11171 0.10598 0.0200 1.0000 0.0635
-9.000 -0.5793 0.10327 0.09759 0.0084 1.0000 0.0552
-8.750 -0.5679 0.09925 0.09357 0.0083 1.0000 0.0541
-8.500 -0.5614 0.09447 0.08881 0.0051 1.0000 0.0531
-8.250 -0.5570 0.08914 0.08350 0.0002 1.0000 0.0525
-8.000 -0.5534 0.08329 0.07766 -0.0061 1.0000 0.0520
-7.750 -0.5480 0.07673 0.07104 -0.0134 1.0000 0.0516
-7.500 -0.5423 0.07057 0.06476 -0.0194 1.0000 0.0515
-7.250 -0.5353 0.06469 0.05867 -0.0246 1.0000 0.0516
-7.000 -0.5261 0.05919 0.05288 -0.0287 1.0000 0.0517
-6.750 -0.5146 0.05412 0.04744 -0.0316 1.0000 0.0517
-6.500 -0.5011 0.04953 0.04242 -0.0335 1.0000 0.0516
-6.250 -0.4846 0.04540 0.03780 -0.0348 0.9890 0.0517
-6.000 -0.4597 0.04131 0.03310 -0.0368 0.9778 0.0523
-5.750 -0.4311 0.03788 0.02886 -0.0384 0.9699 0.0548
-5.500 -0.4038 0.03510 0.02574 -0.0396 0.9626 0.0577
-5.250 -0.3740 0.03281 0.02310 -0.0406 0.9560 0.0600
-5.000 -0.3450 0.03082 0.02073 -0.0410 0.9494 0.0627
-4.750 -0.3153 0.02932 0.01873 -0.0413 0.9429 0.0681
-4.500 -0.2877 0.02784 0.01720 -0.0414 0.9367 0.0728
-4.250 -0.2603 0.02671 0.01587 -0.0411 0.9302 0.0781
-4.000 -0.2338 0.02581 0.01486 -0.0408 0.9239 0.0869
-3.750 -0.2075 0.02504 0.01389 -0.0404 0.9171 0.0966
-3.500 -0.1815 0.02432 0.01318 -0.0403 0.9107 0.1128
-3.250 -0.1558 0.02357 0.01246 -0.0401 0.9039 0.1398
-3.000 -0.1311 0.02229 0.01179 -0.0403 0.8970 0.2342
-2.750 -0.1128 0.02130 0.01205 -0.0386 0.8904 0.4925
-2.500 -0.0944 0.02132 0.01230 -0.0360 0.8831 0.6193
-2.250 -0.0772 0.02106 0.01226 -0.0330 0.8760 0.7214
-2.000 -0.0474 0.02058 0.01205 -0.0320 0.8701 0.8062
-1.750 0.0267 0.02042 0.01185 -0.0399 0.8656 0.9664
-1.500 0.0640 0.02061 0.01170 -0.0425 0.8590 1.0000
-1.250 0.0883 0.02083 0.01166 -0.0428 0.8507 1.0000
-1.000 0.1127 0.02110 0.01169 -0.0427 0.8429 1.0000
-0.750 0.1370 0.02140 0.01176 -0.0425 0.8352 1.0000
-0.500 0.1618 0.02169 0.01186 -0.0424 0.8270 1.0000
-0.250 0.1857 0.02201 0.01201 -0.0417 0.8196 1.0000
0.000 0.2110 0.02231 0.01217 -0.0417 0.8108 1.0000
0.250 0.2349 0.02262 0.01232 -0.0407 0.8036 1.0000
0.500 0.2601 0.02291 0.01252 -0.0406 0.7935 1.0000
0.750 0.2843 0.02317 0.01269 -0.0399 0.7838 1.0000
1.000 0.3076 0.02335 0.01278 -0.0385 0.7747 1.0000
1.250 0.3319 0.02356 0.01292 -0.0378 0.7627 1.0000
1.500 0.3559 0.02373 0.01305 -0.0370 0.7510 1.0000
1.750 0.3797 0.02384 0.01312 -0.0357 0.7402 1.0000
2.000 0.4030 0.02387 0.01313 -0.0342 0.7301 1.0000
2.250 0.4276 0.02402 0.01327 -0.0334 0.7174 1.0000
2.500 0.4519 0.02412 0.01339 -0.0325 0.7049 1.0000
2.750 0.4761 0.02416 0.01345 -0.0313 0.6924 1.0000
3.000 0.5001 0.02413 0.01346 -0.0299 0.6801 1.0000
3.250 0.5239 0.02402 0.01338 -0.0283 0.6676 1.0000
3.500 0.5476 0.02385 0.01325 -0.0266 0.6546 1.0000
3.750 0.5717 0.02373 0.01319 -0.0251 0.6395 1.0000
4.000 0.5961 0.02366 0.01323 -0.0239 0.6220 1.0000
4.250 0.6203 0.02354 0.01318 -0.0225 0.6035 1.0000
4.500 0.6443 0.02334 0.01304 -0.0208 0.5843 1.0000
4.750 0.6682 0.02315 0.01292 -0.0190 0.5635 1.0000
5.000 0.6924 0.02309 0.01292 -0.0176 0.5385 1.0000
5.250 0.7167 0.02310 0.01296 -0.0163 0.5112 1.0000
5.500 0.7406 0.02318 0.01302 -0.0150 0.4819 1.0000
5.750 0.7644 0.02337 0.01320 -0.0137 0.4510 1.0000
6.000 0.7879 0.02373 0.01346 -0.0127 0.4195 1.0000
6.250 0.8111 0.02426 0.01389 -0.0118 0.3887 1.0000
6.500 0.8339 0.02497 0.01449 -0.0111 0.3593 1.0000
6.750 0.8563 0.02581 0.01530 -0.0106 0.3318 1.0000
7.000 0.8783 0.02675 0.01617 -0.0101 0.3064 1.0000
7.250 0.8998 0.02774 0.01714 -0.0096 0.2826 1.0000
7.500 0.9211 0.02881 0.01824 -0.0092 0.2601 1.0000
7.750 0.9416 0.02990 0.01938 -0.0088 0.2388 1.0000
8.000 0.9616 0.03105 0.02055 -0.0083 0.2194 1.0000
8.250 0.9809 0.03228 0.02188 -0.0079 0.2000 1.0000
8.500 0.9995 0.03356 0.02323 -0.0074 0.1828 1.0000
8.750 1.0174 0.03491 0.02464 -0.0069 0.1671 1.0000
9.000 1.0351 0.03637 0.02624 -0.0062 0.1533 1.0000
9.250 1.0513 0.03793 0.02790 -0.0056 0.1401 1.0000
9.500 1.0667 0.03960 0.02969 -0.0049 0.1283 1.0000
9.750 1.0810 0.04132 0.03147 -0.0042 0.1180 1.0000
10.000 1.0938 0.04313 0.03339 -0.0036 0.1085 1.0000
10.250 1.1058 0.04538 0.03591 -0.0028 0.1002 1.0000
10.500 1.1162 0.04726 0.03776 -0.0022 0.0931 1.0000
10.750 1.1219 0.05001 0.04096 -0.0016 0.0865 1.0000
11.000 1.1295 0.05198 0.04287 -0.0007 0.0813 1.0000
11.250 1.1261 0.05528 0.04657 0.0000 0.0769 1.0000
11.500 1.1233 0.05842 0.04996 0.0004 0.0729 1.0000
11.750 1.1268 0.06088 0.05241 0.0009 0.0693 1.0000
12.000 1.1184 0.06498 0.05677 0.0007 0.0669 1.0000
12.250 1.1028 0.07008 0.06223 -0.0005 0.0653 1.0000
12.500 1.0845 0.07584 0.06827 -0.0025 0.0642 1.0000
12.750 1.0625 0.08266 0.07533 -0.0057 0.0638 1.0000
13.000 1.0349 0.09116 0.08404 -0.0103 0.0643 1.0000
13.250 1.0025 0.10168 0.09472 -0.0166 0.0656 1.0000
13.500 0.9693 0.11376 0.10686 -0.0238 0.0668 1.0000
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Polar data table (+)
Polar graphs
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