HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/9 AIRFOIL (hq159-il) Reynolds number: 100,000 Max Cl/Cd: 51.89 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq159-il-100000.txt Download as CSV file: xf-hq159-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4982 0.09664 0.09183 -0.0193 1.0000 0.0986
-8.750 -0.4941 0.09322 0.08845 -0.0200 1.0000 0.1030
-8.500 -0.5072 0.08946 0.08480 -0.0249 1.0000 0.1070
-8.250 -0.5373 0.08487 0.08030 -0.0341 1.0000 0.1081
-8.000 -0.5070 0.08143 0.07689 -0.0266 1.0000 0.1126
-7.750 -0.4282 0.06824 0.06401 -0.0274 1.0000 0.1281
-7.500 -0.4431 0.06409 0.05995 -0.0298 1.0000 0.1323
-7.250 -0.4939 0.05866 0.05437 -0.0388 1.0000 0.1357
-7.000 -0.4615 0.05481 0.05074 -0.0335 1.0000 0.1411
-6.750 -0.4879 0.04984 0.04560 -0.0374 1.0000 0.1504
-6.500 -0.4701 0.04668 0.04256 -0.0342 1.0000 0.1557
-6.250 -0.4760 0.04276 0.03859 -0.0340 1.0000 0.1667
-6.000 -0.5038 0.04088 0.03460 -0.0398 1.0000 0.0699
-5.750 -0.4886 0.03621 0.02907 -0.0374 1.0000 0.0556
-5.500 -0.4725 0.03336 0.02591 -0.0356 1.0000 0.0544
-5.250 -0.4571 0.03050 0.02260 -0.0340 1.0000 0.0556
-5.000 -0.4406 0.02766 0.01966 -0.0328 1.0000 0.0587
-4.750 -0.4206 0.02532 0.01687 -0.0311 1.0000 0.0590
-4.500 -0.3998 0.02339 0.01469 -0.0296 1.0000 0.0613
-4.250 -0.3782 0.02186 0.01287 -0.0281 1.0000 0.0662
-4.000 -0.3578 0.02038 0.01138 -0.0269 1.0000 0.0771
-3.750 -0.3367 0.01885 0.00986 -0.0255 1.0000 0.0906
-3.500 -0.3167 0.01762 0.00877 -0.0243 1.0000 0.1154
-3.250 -0.2967 0.01658 0.00789 -0.0231 1.0000 0.1504
-3.000 -0.2777 0.01469 0.00692 -0.0223 1.0000 0.2789
-2.750 -0.2700 0.01340 0.00732 -0.0178 1.0000 0.6621
-2.500 -0.2585 0.01351 0.00753 -0.0138 1.0000 0.7385
-2.250 -0.2472 0.01360 0.00764 -0.0099 1.0000 0.7917
-2.000 -0.2362 0.01361 0.00766 -0.0059 1.0000 0.8385
-1.750 -0.2233 0.01356 0.00762 -0.0024 1.0000 0.8867
-1.500 -0.1721 0.01368 0.00763 -0.0059 1.0000 0.9625
-1.250 -0.1266 0.01372 0.00745 -0.0110 1.0000 1.0000
-1.000 -0.1079 0.01374 0.00729 -0.0115 0.9984 1.0000
-0.750 -0.0622 0.01409 0.00741 -0.0163 0.9900 1.0000
-0.500 -0.0147 0.01451 0.00764 -0.0214 0.9822 1.0000
-0.250 0.0267 0.01479 0.00779 -0.0251 0.9727 1.0000
0.000 0.0695 0.01512 0.00798 -0.0289 0.9638 1.0000
0.250 0.1156 0.01544 0.00821 -0.0332 0.9557 1.0000
0.500 0.1532 0.01569 0.00839 -0.0358 0.9453 1.0000
0.750 0.1941 0.01593 0.00860 -0.0389 0.9357 1.0000
1.000 0.2460 0.01606 0.00871 -0.0437 0.9267 1.0000
1.250 0.2995 0.01594 0.00861 -0.0484 0.9140 1.0000
1.500 0.3515 0.01568 0.00842 -0.0524 0.9006 1.0000
1.750 0.3915 0.01557 0.00835 -0.0544 0.8877 1.0000
2.000 0.4270 0.01552 0.00835 -0.0554 0.8749 1.0000
2.250 0.4608 0.01544 0.00833 -0.0560 0.8616 1.0000
2.500 0.4926 0.01535 0.00833 -0.0560 0.8477 1.0000
2.750 0.5228 0.01523 0.00828 -0.0556 0.8328 1.0000
3.000 0.5517 0.01507 0.00819 -0.0548 0.8172 1.0000
3.250 0.5763 0.01500 0.00820 -0.0533 0.7981 1.0000
3.500 0.6022 0.01483 0.00813 -0.0518 0.7784 1.0000
3.750 0.6270 0.01465 0.00802 -0.0500 0.7556 1.0000
4.000 0.6515 0.01442 0.00784 -0.0481 0.7289 1.0000
4.250 0.6751 0.01420 0.00765 -0.0460 0.6961 1.0000
4.500 0.6979 0.01406 0.00754 -0.0438 0.6550 1.0000
4.750 0.7196 0.01404 0.00744 -0.0416 0.6013 1.0000
5.000 0.7400 0.01426 0.00745 -0.0393 0.5329 1.0000
5.250 0.7589 0.01484 0.00766 -0.0372 0.4569 1.0000
5.500 0.7771 0.01567 0.00813 -0.0354 0.3854 1.0000
5.750 0.7948 0.01664 0.00875 -0.0337 0.3196 1.0000
6.000 0.8115 0.01787 0.00968 -0.0320 0.2535 1.0000
6.250 0.8266 0.01940 0.01077 -0.0302 0.1834 1.0000
6.500 0.8439 0.02092 0.01194 -0.0287 0.1420 1.0000
6.750 0.8641 0.02245 0.01338 -0.0274 0.1196 1.0000
7.000 0.8848 0.02399 0.01479 -0.0264 0.1029 1.0000
7.250 0.9085 0.02581 0.01667 -0.0255 0.0916 1.0000
7.500 0.9324 0.02794 0.01894 -0.0246 0.0812 1.0000
7.750 0.9530 0.02993 0.02105 -0.0236 0.0688 1.0000
8.000 0.9708 0.03187 0.02320 -0.0224 0.0561 1.0000
8.250 0.9894 0.03515 0.02665 -0.0213 0.0489 1.0000
8.500 1.0057 0.03849 0.03059 -0.0194 0.0456 1.0000
8.750 1.0185 0.04199 0.03455 -0.0175 0.0434 1.0000
9.000 1.0316 0.04492 0.03758 -0.0164 0.0402 1.0000
9.250 1.0328 0.05059 0.04359 -0.0149 0.0387 1.0000
9.500 1.0320 0.05360 0.04714 -0.0123 0.0380 1.0000
9.750 1.0273 0.05760 0.05155 -0.0101 0.0379 1.0000
10.000 1.0180 0.06174 0.05602 -0.0080 0.0379 1.0000
10.250 1.0056 0.06609 0.06060 -0.0062 0.0382 1.0000
10.500 0.8813 0.06456 0.05998 -0.0005 0.0441 1.0000
10.750 0.8496 0.07150 0.06709 -0.0025 0.0462 1.0000
11.000 0.8238 0.07865 0.07434 -0.0055 0.0476 1.0000
11.250 0.8011 0.08619 0.08195 -0.0091 0.0488 1.0000
11.500 0.7834 0.09375 0.08954 -0.0126 0.0497 1.0000
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Polar data table (+)
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