HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.27 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3510-il-1000000.txt Download as CSV file: xf-hq3510-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3368 0.10453 0.10291 -0.0385 1.0000 0.0084
-9.750 -0.3365 0.10141 0.09982 -0.0387 1.0000 0.0084
-9.500 -0.3386 0.09862 0.09706 -0.0383 1.0000 0.0084
-9.250 -0.3347 0.09528 0.09373 -0.0397 0.9995 0.0084
-9.000 -0.3221 0.09050 0.08896 -0.0443 0.9979 0.0084
-8.750 -0.3091 0.08572 0.08418 -0.0492 0.9949 0.0085
-8.500 -0.2976 0.08098 0.07944 -0.0538 0.9907 0.0085
-8.250 -0.2848 0.07571 0.07419 -0.0596 0.9863 0.0085
-8.000 -0.2801 0.06705 0.06555 -0.0697 0.9795 0.0087
-7.750 -0.2596 0.05784 0.05633 -0.0862 0.9716 0.0089
-7.500 -0.2395 0.04939 0.04773 -0.1002 0.9590 0.0091
-7.250 -0.2266 0.04486 0.04305 -0.1046 0.9454 0.0093
-7.000 -0.2161 0.04076 0.03878 -0.1067 0.9324 0.0094
-6.750 -0.2034 0.03738 0.03522 -0.1077 0.9217 0.0097
-6.500 -0.1887 0.03382 0.03144 -0.1085 0.9124 0.0101
-6.250 -0.1872 0.02013 0.01662 -0.1078 0.9005 0.0088
-6.000 -0.1648 0.01779 0.01395 -0.1075 0.8936 0.0087
-5.750 -0.1421 0.01531 0.01106 -0.1071 0.8875 0.0087
-5.500 -0.1175 0.01360 0.00909 -0.1068 0.8815 0.0088
-5.250 -0.0921 0.01228 0.00754 -0.1065 0.8757 0.0088
-5.000 -0.0663 0.01115 0.00623 -0.1062 0.8704 0.0090
-4.750 -0.0403 0.01026 0.00523 -0.1060 0.8644 0.0095
-4.500 -0.0137 0.00962 0.00446 -0.1057 0.8591 0.0097
-4.250 0.0132 0.00903 0.00378 -0.1056 0.8534 0.0098
-4.000 0.0404 0.00857 0.00322 -0.1054 0.8476 0.0101
-3.750 0.0680 0.00821 0.00278 -0.1053 0.8423 0.0108
-3.500 0.0957 0.00791 0.00242 -0.1052 0.8361 0.0121
-3.250 0.1234 0.00769 0.00210 -0.1051 0.8301 0.0133
-3.000 0.1512 0.00742 0.00183 -0.1050 0.8226 0.0188
-2.750 0.1787 0.00724 0.00169 -0.1050 0.8148 0.0382
-2.500 0.2064 0.00711 0.00156 -0.1049 0.8058 0.0495
-2.250 0.2342 0.00699 0.00144 -0.1049 0.7974 0.0617
-2.000 0.2618 0.00685 0.00133 -0.1048 0.7893 0.0860
-1.750 0.2890 0.00641 0.00121 -0.1050 0.7813 0.1961
-1.500 0.3149 0.00560 0.00109 -0.1052 0.7737 0.4461
-1.250 0.3421 0.00537 0.00108 -0.1052 0.7649 0.5367
-1.000 0.3698 0.00531 0.00107 -0.1051 0.7569 0.5794
-0.750 0.3975 0.00529 0.00106 -0.1050 0.7485 0.6074
-0.500 0.4252 0.00529 0.00106 -0.1050 0.7388 0.6294
-0.250 0.4527 0.00528 0.00108 -0.1048 0.7292 0.6580
0.000 0.4800 0.00530 0.00111 -0.1046 0.7199 0.6859
0.250 0.5074 0.00530 0.00115 -0.1045 0.7111 0.7112
0.500 0.5349 0.00533 0.00118 -0.1044 0.7017 0.7250
0.750 0.5624 0.00539 0.00119 -0.1042 0.6910 0.7336
1.000 0.5900 0.00543 0.00122 -0.1042 0.6801 0.7423
1.250 0.6175 0.00547 0.00125 -0.1041 0.6694 0.7508
1.500 0.6448 0.00553 0.00129 -0.1039 0.6572 0.7602
1.750 0.6718 0.00560 0.00134 -0.1038 0.6435 0.7699
2.000 0.6986 0.00567 0.00140 -0.1036 0.6287 0.7798
2.250 0.7252 0.00576 0.00146 -0.1033 0.6116 0.7907
2.500 0.7513 0.00588 0.00153 -0.1030 0.5908 0.8028
2.750 0.7768 0.00602 0.00162 -0.1025 0.5661 0.8165
3.000 0.8015 0.00620 0.00174 -0.1019 0.5352 0.8328
3.250 0.8251 0.00641 0.00187 -0.1011 0.4984 0.8546
3.500 0.8457 0.00655 0.00202 -0.0996 0.4602 0.9061
3.750 0.8749 0.00683 0.00220 -0.1002 0.4193 1.0000
4.000 0.8991 0.00721 0.00241 -0.0997 0.3815 1.0000
4.250 0.9231 0.00760 0.00262 -0.0991 0.3436 1.0000
4.500 0.9471 0.00799 0.00285 -0.0986 0.3095 1.0000
4.750 0.9713 0.00835 0.00308 -0.0981 0.2842 1.0000
5.000 0.9963 0.00863 0.00331 -0.0977 0.2678 1.0000
5.250 1.0214 0.00890 0.00352 -0.0973 0.2535 1.0000
5.500 1.0463 0.00918 0.00374 -0.0970 0.2391 1.0000
5.750 1.0712 0.00945 0.00396 -0.0966 0.2247 1.0000
6.000 1.0960 0.00972 0.00418 -0.0962 0.2109 1.0000
6.250 1.1199 0.01005 0.00444 -0.0956 0.1915 1.0000
6.500 1.1431 0.01045 0.00472 -0.0950 0.1675 1.0000
6.750 1.1643 0.01099 0.00508 -0.0941 0.1368 1.0000
7.000 1.1845 0.01161 0.00553 -0.0930 0.1060 1.0000
7.250 1.2032 0.01235 0.00607 -0.0916 0.0738 1.0000
7.500 1.2194 0.01331 0.00679 -0.0899 0.0369 1.0000
7.750 1.2334 0.01447 0.00773 -0.0878 0.0070 1.0000
8.000 1.2540 0.01502 0.00830 -0.0866 0.0050 1.0000
8.250 1.2749 0.01551 0.00886 -0.0856 0.0046 1.0000
8.500 1.2948 0.01606 0.00947 -0.0843 0.0044 1.0000
8.750 1.3138 0.01665 0.01013 -0.0830 0.0042 1.0000
9.000 1.3319 0.01728 0.01083 -0.0815 0.0040 1.0000
9.250 1.3480 0.01796 0.01160 -0.0797 0.0038 1.0000
9.500 1.3611 0.01872 0.01243 -0.0774 0.0036 1.0000
9.750 1.3718 0.01958 0.01338 -0.0747 0.0035 1.0000
10.000 1.3804 0.02057 0.01448 -0.0718 0.0034 1.0000
10.250 1.3877 0.02165 0.01567 -0.0689 0.0033 1.0000
10.500 1.3914 0.02300 0.01714 -0.0656 0.0032 1.0000
10.750 1.3951 0.02438 0.01863 -0.0626 0.0032 1.0000
11.000 1.3945 0.02614 0.02053 -0.0593 0.0032 1.0000
11.250 1.3931 0.02809 0.02260 -0.0562 0.0031 1.0000
11.500 1.4027 0.02923 0.02382 -0.0545 0.0031 1.0000
11.750 1.4075 0.03082 0.02551 -0.0525 0.0031 1.0000
12.000 1.4110 0.03258 0.02739 -0.0506 0.0030 1.0000
12.250 1.4170 0.03418 0.02910 -0.0490 0.0030 1.0000
12.500 1.4180 0.03634 0.03138 -0.0473 0.0029 1.0000
12.750 1.4166 0.03884 0.03400 -0.0457 0.0029 1.0000
13.000 1.4184 0.04109 0.03638 -0.0446 0.0028 1.0000
13.250 1.4182 0.04367 0.03907 -0.0436 0.0028 1.0000
13.500 1.4151 0.04670 0.04224 -0.0428 0.0027 1.0000
13.750 1.4114 0.04994 0.04562 -0.0423 0.0026 1.0000
14.000 1.4056 0.05362 0.04943 -0.0420 0.0026 1.0000
14.250 1.3998 0.05747 0.05343 -0.0422 0.0025 1.0000
14.500 1.3921 0.06182 0.05793 -0.0428 0.0025 1.0000
14.750 1.3823 0.06672 0.06299 -0.0437 0.0025 1.0000
15.000 1.3724 0.07190 0.06832 -0.0452 0.0025 1.0000
15.250 1.3612 0.07761 0.07419 -0.0472 0.0025 1.0000
15.500 1.3476 0.08405 0.08080 -0.0498 0.0025 1.0000
15.750 1.3348 0.09065 0.08755 -0.0528 0.0025 1.0000
16.000 1.3201 0.09794 0.09501 -0.0564 0.0025 1.0000
16.250 1.3040 0.10585 0.10309 -0.0605 0.0025 1.0000
16.500 1.2887 0.11385 0.11124 -0.0649 0.0026 1.0000
16.750 1.2740 0.12202 0.11956 -0.0696 0.0026 1.0000
17.000 1.2581 0.13074 0.12843 -0.0748 0.0026 1.0000
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