HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Reynolds number: 100,000 Max Cl/Cd: 45.46 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hh02-il-100000-n5.txt Download as CSV file: xf-hh02-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6039 0.08977 0.08572 0.0160 0.8997 0.0283
-8.000 -0.6065 0.08359 0.07956 0.0100 0.8948 0.0279
-7.750 -0.6069 0.07502 0.07096 0.0003 0.8903 0.0273
-7.500 -0.6051 0.06680 0.06254 -0.0072 0.8857 0.0271
-7.250 -0.5991 0.06121 0.05672 -0.0109 0.8814 0.0276
-7.000 -0.5886 0.05550 0.05069 -0.0143 0.8768 0.0282
-6.750 -0.5774 0.05029 0.04505 -0.0160 0.8726 0.0287
-6.500 -0.5618 0.04515 0.03940 -0.0175 0.8682 0.0287
-6.250 -0.5436 0.04074 0.03444 -0.0181 0.8638 0.0290
-6.000 -0.5248 0.03721 0.03035 -0.0176 0.8599 0.0294
-5.750 -0.5000 0.03397 0.02654 -0.0180 0.8551 0.0304
-5.500 -0.4753 0.03179 0.02372 -0.0176 0.8506 0.0326
-5.250 -0.4528 0.02958 0.02121 -0.0170 0.8467 0.0342
-5.000 -0.4249 0.02775 0.01914 -0.0174 0.8417 0.0356
-4.750 -0.3989 0.02627 0.01744 -0.0170 0.8371 0.0372
-4.500 -0.3745 0.02518 0.01613 -0.0161 0.8334 0.0401
-4.250 -0.3453 0.02417 0.01484 -0.0162 0.8282 0.0432
-4.000 -0.3198 0.02272 0.01341 -0.0158 0.8235 0.0459
-3.750 -0.2955 0.02188 0.01251 -0.0149 0.8197 0.0496
-3.500 -0.2679 0.02121 0.01170 -0.0148 0.8148 0.0551
-3.250 -0.2416 0.02032 0.01083 -0.0146 0.8098 0.0607
-3.000 -0.2166 0.01976 0.01017 -0.0138 0.8057 0.0695
-2.750 -0.1902 0.01914 0.00954 -0.0134 0.8013 0.0833
-2.500 -0.1625 0.01839 0.00900 -0.0137 0.7958 0.1201
-2.250 -0.1382 0.01732 0.00853 -0.0133 0.7916 0.2525
-2.000 -0.1149 0.01640 0.00849 -0.0125 0.7874 0.4699
-1.750 -0.0874 0.01621 0.00850 -0.0122 0.7813 0.5685
-1.500 -0.0644 0.01602 0.00847 -0.0106 0.7769 0.6489
-1.250 -0.0399 0.01579 0.00831 -0.0094 0.7724 0.7050
-1.000 -0.0112 0.01556 0.00811 -0.0094 0.7661 0.7395
-0.750 0.0153 0.01513 0.00786 -0.0083 0.7617 0.7900
-0.500 0.0792 0.01483 0.00778 -0.0149 0.7576 0.9997
-0.250 0.1086 0.01491 0.00770 -0.0155 0.7506 1.0000
0.000 0.1333 0.01490 0.00753 -0.0146 0.7459 1.0000
0.250 0.1621 0.01496 0.00747 -0.0149 0.7377 1.0000
0.500 0.1859 0.01485 0.00723 -0.0136 0.7310 1.0000
0.750 0.2134 0.01482 0.00710 -0.0134 0.7210 1.0000
1.000 0.2363 0.01466 0.00682 -0.0117 0.7145 1.0000
1.250 0.2651 0.01469 0.00680 -0.0119 0.7041 1.0000
1.500 0.2911 0.01465 0.00668 -0.0112 0.6964 1.0000
1.750 0.3177 0.01462 0.00660 -0.0107 0.6876 1.0000
2.000 0.3450 0.01462 0.00657 -0.0104 0.6781 1.0000
2.250 0.3697 0.01451 0.00640 -0.0092 0.6703 1.0000
2.500 0.3978 0.01454 0.00643 -0.0091 0.6587 1.0000
2.750 0.4248 0.01453 0.00640 -0.0087 0.6471 1.0000
3.000 0.4511 0.01449 0.00636 -0.0080 0.6352 1.0000
3.250 0.4775 0.01445 0.00630 -0.0074 0.6220 1.0000
3.500 0.5042 0.01445 0.00628 -0.0068 0.6066 1.0000
3.750 0.5312 0.01447 0.00629 -0.0064 0.5889 1.0000
4.000 0.5580 0.01450 0.00632 -0.0059 0.5695 1.0000
4.250 0.5849 0.01456 0.00635 -0.0054 0.5479 1.0000
4.500 0.6121 0.01468 0.00643 -0.0051 0.5226 1.0000
4.750 0.6394 0.01485 0.00655 -0.0049 0.4934 1.0000
5.000 0.6666 0.01510 0.00672 -0.0048 0.4605 1.0000
5.250 0.6940 0.01544 0.00696 -0.0048 0.4238 1.0000
5.500 0.7211 0.01590 0.00726 -0.0049 0.3874 1.0000
5.750 0.7482 0.01646 0.00768 -0.0052 0.3546 1.0000
6.000 0.7751 0.01706 0.00818 -0.0055 0.3251 1.0000
6.250 0.8018 0.01768 0.00873 -0.0059 0.2990 1.0000
6.500 0.8282 0.01832 0.00933 -0.0062 0.2750 1.0000
6.750 0.8542 0.01899 0.00998 -0.0065 0.2525 1.0000
7.000 0.8800 0.01966 0.01065 -0.0067 0.2308 1.0000
7.250 0.9053 0.02038 0.01135 -0.0070 0.2098 1.0000
7.500 0.9299 0.02114 0.01209 -0.0072 0.1907 1.0000
7.750 0.9542 0.02191 0.01292 -0.0074 0.1729 1.0000
8.000 0.9778 0.02275 0.01378 -0.0074 0.1570 1.0000
8.250 1.0006 0.02365 0.01471 -0.0075 0.1416 1.0000
8.500 1.0227 0.02461 0.01570 -0.0075 0.1269 1.0000
8.750 1.0438 0.02563 0.01680 -0.0074 0.1140 1.0000
9.000 1.0639 0.02674 0.01795 -0.0073 0.1026 1.0000
9.250 1.0825 0.02798 0.01919 -0.0071 0.0929 1.0000
9.500 1.1009 0.02917 0.02051 -0.0069 0.0833 1.0000
9.750 1.1177 0.03053 0.02197 -0.0065 0.0755 1.0000
10.000 1.1315 0.03206 0.02351 -0.0063 0.0687 1.0000
10.250 1.1463 0.03349 0.02516 -0.0058 0.0620 1.0000
10.500 1.1558 0.03526 0.02694 -0.0054 0.0569 1.0000
10.750 1.1656 0.03688 0.02878 -0.0045 0.0518 1.0000
11.000 1.1713 0.03868 0.03067 -0.0036 0.0479 1.0000
11.250 1.1751 0.04081 0.03287 -0.0027 0.0445 1.0000
11.500 1.1804 0.04291 0.03519 -0.0020 0.0408 1.0000
11.750 1.1829 0.04522 0.03760 -0.0016 0.0380 1.0000
12.000 1.1820 0.04797 0.04037 -0.0014 0.0358 1.0000
12.250 1.1836 0.05073 0.04343 -0.0011 0.0335 1.0000
12.500 1.1827 0.05379 0.04672 -0.0012 0.0316 1.0000
12.750 1.1802 0.05705 0.05013 -0.0016 0.0300 1.0000
13.000 1.1761 0.06056 0.05375 -0.0024 0.0288 1.0000
13.250 1.1700 0.06444 0.05770 -0.0033 0.0278 1.0000
13.500 1.1621 0.06899 0.06250 -0.0047 0.0269 1.0000
13.750 1.1520 0.07404 0.06781 -0.0066 0.0261 1.0000
14.000 1.1400 0.07963 0.07363 -0.0091 0.0254 1.0000
14.250 1.1263 0.08586 0.08007 -0.0122 0.0250 1.0000
14.500 1.1105 0.09286 0.08728 -0.0159 0.0247 1.0000
14.750 1.0921 0.10080 0.09542 -0.0203 0.0246 1.0000
15.000 1.0703 0.10996 0.10477 -0.0256 0.0248 1.0000
15.250 1.0442 0.12072 0.11571 -0.0318 0.0253 1.0000
15.500 1.0141 0.13314 0.12823 -0.0389 0.0261 1.0000
15.750 0.9806 0.14758 0.14275 -0.0468 0.0269 1.0000
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Polar data table (+)
Polar graphs
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