HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 200,000 Max Cl/Cd: 77.7 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3512-il-200000-n5.txt Download as CSV file: xf-hq3512-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3417 0.10008 0.09657 -0.0464 1.0000 0.0145
-10.000 -0.3470 0.09674 0.09329 -0.0464 1.0000 0.0143
-9.750 -0.3549 0.09375 0.09036 -0.0458 1.0000 0.0142
-9.500 -0.3535 0.08854 0.08520 -0.0494 0.9968 0.0142
-9.250 -0.3487 0.08220 0.07887 -0.0554 0.9903 0.0143
-9.000 -0.3454 0.07464 0.07133 -0.0632 0.9842 0.0146
-8.750 -0.3462 0.06574 0.06246 -0.0731 0.9746 0.0144
-8.500 -0.3544 0.05208 0.04860 -0.0919 0.9598 0.0141
-8.250 -0.3616 0.04223 0.03827 -0.1000 0.9466 0.0140
-8.000 -0.3611 0.03460 0.02997 -0.1032 0.9356 0.0143
-7.750 -0.3459 0.02925 0.02391 -0.1051 0.9293 0.0143
-7.500 -0.3299 0.02597 0.02009 -0.1049 0.9209 0.0146
-7.250 -0.3052 0.02345 0.01711 -0.1055 0.9162 0.0149
-7.000 -0.2822 0.02168 0.01500 -0.1052 0.9098 0.0153
-6.750 -0.2569 0.02020 0.01327 -0.1052 0.9043 0.0157
-6.500 -0.2295 0.01907 0.01201 -0.1056 0.9001 0.0165
-6.250 -0.2057 0.01832 0.01114 -0.1051 0.8931 0.0173
-6.000 -0.1787 0.01751 0.01020 -0.1051 0.8881 0.0184
-5.750 -0.1528 0.01686 0.00942 -0.1049 0.8824 0.0205
-5.500 -0.1272 0.01627 0.00880 -0.1047 0.8764 0.0228
-5.250 -0.0994 0.01568 0.00810 -0.1047 0.8720 0.0268
-5.000 -0.0748 0.01510 0.00749 -0.1043 0.8652 0.0318
-4.750 -0.0477 0.01469 0.00697 -0.1042 0.8600 0.0381
-4.500 -0.0203 0.01437 0.00661 -0.1042 0.8550 0.0446
-4.250 0.0058 0.01412 0.00636 -0.1040 0.8486 0.0534
-4.000 0.0339 0.01390 0.00603 -0.1041 0.8438 0.0608
-3.750 0.0599 0.01352 0.00566 -0.1039 0.8379 0.0685
-3.500 0.0869 0.01323 0.00530 -0.1038 0.8321 0.0764
-3.250 0.1150 0.01290 0.00493 -0.1039 0.8276 0.0878
-3.000 0.1408 0.01261 0.00467 -0.1036 0.8209 0.1060
-2.750 0.1679 0.01221 0.00440 -0.1037 0.8156 0.1487
-2.500 0.1938 0.01163 0.00417 -0.1037 0.8100 0.2537
-2.250 0.2176 0.01087 0.00409 -0.1035 0.8037 0.4466
-2.000 0.2441 0.01065 0.00412 -0.1030 0.7989 0.5467
-1.750 0.2698 0.01063 0.00417 -0.1025 0.7918 0.5896
-1.500 0.2973 0.01062 0.00413 -0.1021 0.7860 0.6211
-1.250 0.3228 0.01065 0.00422 -0.1014 0.7790 0.6581
-1.000 0.3488 0.01069 0.00427 -0.1006 0.7720 0.6904
-0.750 0.3751 0.01071 0.00426 -0.1000 0.7636 0.7071
-0.500 0.4028 0.01068 0.00414 -0.0997 0.7556 0.7162
-0.250 0.4295 0.01068 0.00409 -0.0994 0.7456 0.7243
0.000 0.4566 0.01067 0.00403 -0.0991 0.7370 0.7311
0.250 0.4840 0.01067 0.00396 -0.0989 0.7282 0.7392
0.500 0.5105 0.01068 0.00396 -0.0985 0.7192 0.7461
0.750 0.5381 0.01070 0.00391 -0.0984 0.7105 0.7544
1.000 0.5643 0.01070 0.00391 -0.0979 0.7002 0.7618
1.250 0.5908 0.01073 0.00390 -0.0976 0.6894 0.7703
1.500 0.6172 0.01075 0.00391 -0.0972 0.6799 0.7784
1.750 0.6438 0.01078 0.00394 -0.0969 0.6705 0.7872
2.000 0.6700 0.01082 0.00398 -0.0965 0.6600 0.7965
2.250 0.6957 0.01086 0.00402 -0.0959 0.6489 0.8058
2.500 0.7214 0.01090 0.00407 -0.0954 0.6372 0.8162
3.000 0.7716 0.01100 0.00419 -0.0942 0.6107 0.8408
3.250 0.7964 0.01105 0.00425 -0.0935 0.5949 0.8561
3.500 0.8206 0.01110 0.00434 -0.0926 0.5764 0.8767
3.750 0.8475 0.01115 0.00441 -0.0924 0.5559 0.9136
4.000 0.8778 0.01131 0.00451 -0.0931 0.5308 1.0000
4.250 0.9013 0.01160 0.00467 -0.0924 0.5033 1.0000
4.500 0.9237 0.01195 0.00489 -0.0915 0.4741 1.0000
4.750 0.9450 0.01236 0.00515 -0.0904 0.4438 1.0000
5.000 0.9655 0.01282 0.00545 -0.0893 0.4139 1.0000
5.250 0.9858 0.01329 0.00580 -0.0881 0.3860 1.0000
5.500 1.0057 0.01379 0.00617 -0.0869 0.3599 1.0000
5.750 1.0258 0.01427 0.00655 -0.0858 0.3369 1.0000
6.000 1.0456 0.01477 0.00696 -0.0846 0.3174 1.0000
6.250 1.0657 0.01525 0.00739 -0.0835 0.3022 1.0000
6.500 1.0854 0.01574 0.00783 -0.0823 0.2893 1.0000
6.750 1.1054 0.01621 0.00828 -0.0812 0.2783 1.0000
7.000 1.1255 0.01668 0.00875 -0.0801 0.2682 1.0000
7.250 1.1446 0.01718 0.00924 -0.0788 0.2591 1.0000
7.500 1.1635 0.01766 0.00975 -0.0775 0.2495 1.0000
7.750 1.1821 0.01811 0.01024 -0.0762 0.2407 1.0000
8.000 1.1987 0.01864 0.01077 -0.0745 0.2326 1.0000
8.250 1.2177 0.01907 0.01128 -0.0733 0.2245 1.0000
8.500 1.2341 0.01962 0.01185 -0.0717 0.2169 1.0000
8.750 1.2506 0.02014 0.01244 -0.0701 0.2055 1.0000
9.000 1.2669 0.02068 0.01303 -0.0686 0.1935 1.0000
9.250 1.2819 0.02129 0.01366 -0.0670 0.1802 1.0000
9.500 1.2964 0.02196 0.01434 -0.0653 0.1670 1.0000
9.750 1.3092 0.02275 0.01511 -0.0636 0.1516 1.0000
10.000 1.3199 0.02369 0.01599 -0.0617 0.1346 1.0000
10.250 1.3292 0.02479 0.01702 -0.0597 0.1147 1.0000
10.500 1.3375 0.02600 0.01816 -0.0578 0.0978 1.0000
10.750 1.3461 0.02724 0.01936 -0.0560 0.0844 1.0000
11.000 1.3544 0.02854 0.02065 -0.0543 0.0721 1.0000
11.250 1.3619 0.02994 0.02204 -0.0526 0.0607 1.0000
11.500 1.3676 0.03152 0.02360 -0.0509 0.0490 1.0000
11.750 1.3731 0.03317 0.02526 -0.0493 0.0384 1.0000
12.000 1.3750 0.03518 0.02724 -0.0476 0.0268 1.0000
12.250 1.3759 0.03735 0.02942 -0.0460 0.0194 1.0000
12.500 1.3753 0.03974 0.03185 -0.0445 0.0143 1.0000
12.750 1.3743 0.04224 0.03444 -0.0432 0.0117 1.0000
13.000 1.3763 0.04454 0.03689 -0.0422 0.0103 1.0000
13.250 1.3759 0.04717 0.03963 -0.0414 0.0091 1.0000
13.500 1.3747 0.04997 0.04258 -0.0408 0.0086 1.0000
13.750 1.3711 0.05318 0.04592 -0.0403 0.0082 1.0000
14.000 1.3692 0.05633 0.04924 -0.0402 0.0079 1.0000
14.250 1.3657 0.05981 0.05289 -0.0402 0.0076 1.0000
14.500 1.3609 0.06362 0.05687 -0.0406 0.0073 1.0000
14.750 1.3550 0.06776 0.06118 -0.0413 0.0071 1.0000
15.000 1.3482 0.07221 0.06581 -0.0424 0.0070 1.0000
15.250 1.3401 0.07707 0.07084 -0.0437 0.0069 1.0000
15.500 1.3311 0.08227 0.07621 -0.0455 0.0068 1.0000
15.750 1.3207 0.08792 0.08203 -0.0476 0.0067 1.0000
16.000 1.3096 0.09392 0.08820 -0.0501 0.0066 1.0000
16.250 1.2981 0.10017 0.09462 -0.0529 0.0065 1.0000
16.500 1.2858 0.10675 0.10136 -0.0559 0.0064 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HQ 3.5/12 AIRFOIL (hq3512-il)