HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.68 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq209-il-1000000.txt Download as CSV file: xf-hq209-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4575 0.08311 0.08153 -0.0291 1.0000 0.0079
-8.750 -0.4586 0.07872 0.07716 -0.0314 1.0000 0.0079
-8.500 -0.4611 0.07412 0.07259 -0.0339 1.0000 0.0079
-7.000 -0.4765 0.02073 0.01727 -0.0636 0.9829 0.0060
-6.750 -0.4477 0.01890 0.01519 -0.0646 0.9770 0.0066
-6.500 -0.4181 0.01674 0.01271 -0.0656 0.9714 0.0070
-6.250 -0.3896 0.01521 0.01093 -0.0661 0.9641 0.0073
-6.000 -0.3620 0.01379 0.00929 -0.0663 0.9560 0.0074
-5.750 -0.3364 0.01285 0.00819 -0.0659 0.9459 0.0076
-5.500 -0.3095 0.01257 0.00782 -0.0657 0.9367 0.0079
-5.250 -0.2863 0.01099 0.00600 -0.0648 0.9271 0.0083
-5.000 -0.2624 0.00990 0.00475 -0.0640 0.9174 0.0086
-4.750 -0.2373 0.00916 0.00388 -0.0635 0.9091 0.0092
-4.500 -0.2112 0.00875 0.00339 -0.0631 0.9012 0.0104
-4.250 -0.1844 0.00843 0.00300 -0.0628 0.8936 0.0117
-4.000 -0.1575 0.00822 0.00270 -0.0626 0.8865 0.0127
-3.750 -0.1308 0.00778 0.00221 -0.0623 0.8791 0.0187
-3.250 -0.0766 0.00732 0.00181 -0.0619 0.8648 0.0512
-2.750 -0.0225 0.00688 0.00150 -0.0617 0.8494 0.1071
-2.500 0.0038 0.00645 0.00133 -0.0616 0.8420 0.1951
-2.250 0.0294 0.00583 0.00116 -0.0615 0.8339 0.3379
-2.000 0.0551 0.00531 0.00106 -0.0614 0.8253 0.4819
-1.750 0.0819 0.00512 0.00100 -0.0612 0.8159 0.5453
-1.500 0.1093 0.00502 0.00096 -0.0610 0.8060 0.5832
-1.250 0.1369 0.00496 0.00093 -0.0609 0.7966 0.6108
-1.000 0.1644 0.00492 0.00091 -0.0607 0.7874 0.6399
-0.750 0.1919 0.00490 0.00089 -0.0606 0.7770 0.6637
-0.500 0.2194 0.00487 0.00089 -0.0604 0.7663 0.6861
-0.250 0.2469 0.00486 0.00089 -0.0602 0.7553 0.7068
0.000 0.2743 0.00487 0.00089 -0.0600 0.7438 0.7233
0.250 0.3017 0.00488 0.00091 -0.0599 0.7330 0.7392
0.500 0.3292 0.00489 0.00093 -0.0597 0.7218 0.7556
0.750 0.3567 0.00491 0.00094 -0.0596 0.7094 0.7677
1.000 0.3843 0.00494 0.00096 -0.0594 0.6965 0.7775
1.250 0.4118 0.00499 0.00099 -0.0593 0.6829 0.7882
1.500 0.4389 0.00503 0.00102 -0.0591 0.6678 0.7990
2.000 0.4929 0.00514 0.00110 -0.0586 0.6333 0.8232
2.250 0.5194 0.00521 0.00116 -0.0583 0.6120 0.8377
2.500 0.5453 0.00529 0.00123 -0.0579 0.5862 0.8548
2.750 0.5698 0.00542 0.00131 -0.0572 0.5475 0.8785
3.000 0.5918 0.00560 0.00142 -0.0559 0.4893 0.9290
3.250 0.6273 0.00604 0.00158 -0.0579 0.4144 1.0000
3.500 0.6523 0.00642 0.00176 -0.0575 0.3639 1.0000
3.750 0.6772 0.00682 0.00195 -0.0572 0.3138 1.0000
4.000 0.7021 0.00722 0.00216 -0.0568 0.2710 1.0000
4.250 0.7278 0.00752 0.00235 -0.0565 0.2457 1.0000
4.500 0.7538 0.00779 0.00254 -0.0563 0.2247 1.0000
4.750 0.7799 0.00804 0.00273 -0.0561 0.2047 1.0000
5.000 0.8049 0.00841 0.00295 -0.0557 0.1712 1.0000
5.250 0.8286 0.00894 0.00324 -0.0552 0.1261 1.0000
5.500 0.8516 0.00955 0.00362 -0.0546 0.0818 1.0000
5.750 0.8758 0.01002 0.00398 -0.0541 0.0584 1.0000
6.000 0.9005 0.01040 0.00430 -0.0537 0.0454 1.0000
6.250 0.9257 0.01073 0.00460 -0.0534 0.0375 1.0000
6.500 0.9506 0.01109 0.00493 -0.0530 0.0304 1.0000
6.750 0.9756 0.01143 0.00523 -0.0526 0.0235 1.0000
7.000 0.9988 0.01199 0.00569 -0.0520 0.0106 1.0000
7.250 1.0219 0.01257 0.00624 -0.0513 0.0059 1.0000
7.500 1.0459 0.01303 0.00676 -0.0507 0.0049 1.0000
7.750 1.0696 0.01350 0.00729 -0.0501 0.0046 1.0000
8.000 1.0930 0.01401 0.00787 -0.0494 0.0044 1.0000
8.250 1.1157 0.01457 0.00851 -0.0486 0.0042 1.0000
8.500 1.1378 0.01518 0.00921 -0.0478 0.0039 1.0000
8.750 1.1591 0.01588 0.00999 -0.0469 0.0037 1.0000
9.000 1.1793 0.01667 0.01087 -0.0458 0.0034 1.0000
9.250 1.1973 0.01770 0.01203 -0.0444 0.0031 1.0000
9.500 1.2136 0.01884 0.01331 -0.0428 0.0030 1.0000
9.750 1.2229 0.02074 0.01542 -0.0402 0.0028 1.0000
10.000 1.2363 0.02208 0.01690 -0.0382 0.0028 1.0000
10.250 1.2453 0.02385 0.01887 -0.0358 0.0028 1.0000
10.500 1.2525 0.02573 0.02093 -0.0331 0.0028 1.0000
10.750 1.2582 0.02735 0.02271 -0.0303 0.0028 1.0000
11.000 1.2607 0.02894 0.02446 -0.0270 0.0028 1.0000
11.250 1.2643 0.03037 0.02602 -0.0242 0.0028 1.0000
11.500 1.2651 0.03209 0.02789 -0.0214 0.0028 1.0000
11.750 1.2637 0.03410 0.03006 -0.0188 0.0028 1.0000
12.000 1.2590 0.03652 0.03266 -0.0165 0.0029 1.0000
12.250 1.2569 0.03877 0.03506 -0.0149 0.0029 1.0000
12.500 1.2517 0.04149 0.03795 -0.0135 0.0029 1.0000
12.750 1.2479 0.04425 0.04086 -0.0128 0.0030 1.0000
13.000 1.2362 0.04820 0.04503 -0.0125 0.0030 1.0000
13.250 1.2262 0.05228 0.04928 -0.0130 0.0030 1.0000
13.500 1.2094 0.05779 0.05501 -0.0146 0.0031 1.0000
13.750 1.1712 0.06766 0.06523 -0.0188 0.0034 1.0000
14.000 1.1406 0.07756 0.07536 -0.0245 0.0035 1.0000
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Polar data table (+)
Polar graphs
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