HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il) Reynolds number: 100,000 Max Cl/Cd: 52.4 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2012-il-100000.txt Download as CSV file: xf-hq2012-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/12 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4526 0.09468 0.08988 -0.0389 1.0000 0.1368
-9.250 -0.4399 0.09081 0.08603 -0.0372 1.0000 0.1407
-9.000 -0.4368 0.08804 0.08330 -0.0371 1.0000 0.1489
-8.750 -0.4736 0.08318 0.07863 -0.0429 1.0000 0.1512
-8.500 -0.4438 0.08087 0.07629 -0.0379 1.0000 0.1592
-8.250 -0.4736 0.07707 0.07265 -0.0403 1.0000 0.1643
-8.000 -0.5902 0.05746 0.05262 -0.0485 1.0000 0.0767
-7.750 -0.6251 0.05116 0.04567 -0.0447 1.0000 0.0663
-7.500 -0.6287 0.04772 0.04206 -0.0421 1.0000 0.0649
-7.250 -0.6300 0.04422 0.03827 -0.0397 1.0000 0.0637
-7.000 -0.6277 0.04096 0.03461 -0.0375 1.0000 0.0640
-6.750 -0.6212 0.03807 0.03124 -0.0354 1.0000 0.0656
-6.500 -0.6106 0.03542 0.02804 -0.0335 1.0000 0.0669
-6.250 -0.5966 0.03313 0.02520 -0.0317 1.0000 0.0680
-6.000 -0.5807 0.03006 0.02199 -0.0308 1.0000 0.0711
-5.750 -0.5630 0.02888 0.02068 -0.0296 1.0000 0.0771
-5.500 -0.5432 0.02713 0.01847 -0.0284 1.0000 0.0822
-5.250 -0.5243 0.02586 0.01724 -0.0275 1.0000 0.0899
-5.000 -0.5042 0.02455 0.01577 -0.0264 1.0000 0.0981
-4.750 -0.4814 0.02383 0.01486 -0.0259 0.9991 0.1087
-4.500 -0.4442 0.02281 0.01381 -0.0282 0.9942 0.1234
-4.250 -0.4104 0.02170 0.01286 -0.0298 0.9889 0.1396
-4.000 -0.3742 0.02093 0.01224 -0.0319 0.9837 0.1653
-3.750 -0.3429 0.01996 0.01160 -0.0331 0.9778 0.2076
-3.500 -0.3152 0.01816 0.01101 -0.0343 0.9722 0.3720
-3.250 -0.2908 0.01803 0.01178 -0.0331 0.9656 0.5982
-3.000 -0.2625 0.01856 0.01233 -0.0324 0.9583 0.6623
-2.750 -0.2342 0.01907 0.01277 -0.0318 0.9515 0.7038
-2.500 -0.2080 0.01948 0.01314 -0.0307 0.9440 0.7357
-2.250 -0.1810 0.01986 0.01347 -0.0298 0.9373 0.7650
-2.000 -0.1572 0.02010 0.01367 -0.0284 0.9295 0.7921
-1.750 -0.1316 0.02031 0.01384 -0.0271 0.9228 0.8159
-1.500 -0.1090 0.02039 0.01387 -0.0256 0.9148 0.8386
-1.250 -0.0814 0.02047 0.01391 -0.0250 0.9081 0.8595
-1.000 -0.0576 0.02049 0.01388 -0.0239 0.9000 0.8815
-0.750 -0.0204 0.02060 0.01395 -0.0247 0.8946 0.9065
-0.500 0.0154 0.02076 0.01408 -0.0260 0.8867 0.9285
-0.250 0.0744 0.02087 0.01408 -0.0319 0.8825 0.9412
0.000 0.1216 0.02104 0.01419 -0.0363 0.8752 0.9526
0.250 0.1844 0.02108 0.01417 -0.0433 0.8703 0.9598
0.500 0.2548 0.02092 0.01394 -0.0513 0.8670 0.9650
0.750 0.3094 0.02080 0.01380 -0.0567 0.8573 0.9730
1.000 0.3812 0.02000 0.01296 -0.0638 0.8514 0.9761
1.250 0.4317 0.01954 0.01250 -0.0678 0.8391 0.9846
1.500 0.4823 0.01912 0.01211 -0.0720 0.8279 0.9937
1.750 0.5268 0.01871 0.01170 -0.0752 0.8188 1.0000
2.000 0.5436 0.01853 0.01153 -0.0733 0.8079 1.0000
2.250 0.5503 0.01856 0.01157 -0.0700 0.7947 1.0000
2.500 0.5570 0.01858 0.01159 -0.0666 0.7819 1.0000
2.750 0.5699 0.01854 0.01155 -0.0640 0.7697 1.0000
3.000 0.5932 0.01834 0.01134 -0.0628 0.7586 1.0000
3.250 0.6229 0.01797 0.01095 -0.0623 0.7481 1.0000
3.500 0.6470 0.01784 0.01084 -0.0612 0.7342 1.0000
3.750 0.6731 0.01763 0.01065 -0.0603 0.7199 1.0000
4.000 0.7004 0.01738 0.01040 -0.0594 0.7048 1.0000
4.250 0.7285 0.01709 0.01012 -0.0586 0.6887 1.0000
4.500 0.7518 0.01699 0.01005 -0.0572 0.6677 1.0000
4.750 0.7791 0.01671 0.00976 -0.0561 0.6465 1.0000
5.000 0.8033 0.01656 0.00960 -0.0547 0.6199 1.0000
5.250 0.8275 0.01644 0.00944 -0.0533 0.5890 1.0000
5.500 0.8502 0.01645 0.00934 -0.0517 0.5524 1.0000
5.750 0.8720 0.01664 0.00934 -0.0500 0.5127 1.0000
6.000 0.8922 0.01707 0.00958 -0.0484 0.4725 1.0000
6.250 0.9125 0.01763 0.00992 -0.0469 0.4375 1.0000
6.500 0.9323 0.01826 0.01039 -0.0455 0.4058 1.0000
6.750 0.9522 0.01893 0.01090 -0.0442 0.3780 1.0000
7.000 0.9716 0.01960 0.01148 -0.0429 0.3521 1.0000
7.250 0.9906 0.02029 0.01214 -0.0416 0.3276 1.0000
7.500 1.0092 0.02105 0.01279 -0.0402 0.3042 1.0000
7.750 1.0266 0.02186 0.01354 -0.0388 0.2801 1.0000
8.000 1.0425 0.02275 0.01439 -0.0371 0.2548 1.0000
8.250 1.0568 0.02374 0.01530 -0.0352 0.2284 1.0000
8.500 1.0688 0.02477 0.01626 -0.0331 0.2014 1.0000
8.750 1.0796 0.02583 0.01721 -0.0308 0.1764 1.0000
9.000 1.0917 0.02700 0.01835 -0.0287 0.1553 1.0000
9.250 1.1065 0.02833 0.01960 -0.0270 0.1401 1.0000
9.500 1.1236 0.02977 0.02100 -0.0257 0.1283 1.0000
9.750 1.1427 0.03130 0.02244 -0.0248 0.1186 1.0000
10.000 1.1619 0.03277 0.02403 -0.0238 0.1107 1.0000
10.250 1.1864 0.03479 0.02609 -0.0237 0.1044 1.0000
10.500 1.2041 0.03640 0.02788 -0.0226 0.0986 1.0000
10.750 1.2303 0.03882 0.03024 -0.0229 0.0932 1.0000
11.000 1.2436 0.04091 0.03273 -0.0212 0.0899 1.0000
11.250 1.2574 0.04313 0.03522 -0.0198 0.0865 1.0000
11.500 1.2805 0.04588 0.03790 -0.0201 0.0818 1.0000
11.750 1.2786 0.04836 0.04084 -0.0170 0.0795 1.0000
12.000 1.2720 0.05066 0.04354 -0.0135 0.0772 1.0000
12.250 1.2716 0.05228 0.04531 -0.0109 0.0733 1.0000
12.500 1.2784 0.05462 0.04754 -0.0099 0.0681 1.0000
12.750 1.2582 0.05672 0.05001 -0.0062 0.0664 1.0000
13.000 1.2417 0.05936 0.05294 -0.0038 0.0642 1.0000
13.250 1.2399 0.06123 0.05486 -0.0027 0.0603 1.0000
13.500 1.2417 0.06492 0.05850 -0.0023 0.0567 1.0000
13.750 1.2186 0.06891 0.06281 -0.0013 0.0563 1.0000
14.000 1.1940 0.07358 0.06777 -0.0014 0.0559 1.0000
14.250 1.1685 0.07905 0.07352 -0.0025 0.0558 1.0000
14.500 1.1417 0.08541 0.08012 -0.0046 0.0560 1.0000
14.750 1.1147 0.09247 0.08738 -0.0078 0.0562 1.0000
15.000 1.0878 0.10039 0.09546 -0.0117 0.0567 1.0000
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