HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il) Reynolds number: 200,000 Max Cl/Cd: 67.53 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2195-il-200000-n5.txt Download as CSV file: xf-hq2195-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.1/9.5 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4884 0.08476 0.08108 -0.0356 1.0000 0.0189
-9.500 -0.4941 0.07942 0.07578 -0.0385 1.0000 0.0188
-9.250 -0.5027 0.07340 0.06982 -0.0422 1.0000 0.0187
-9.000 -0.5149 0.06666 0.06313 -0.0475 1.0000 0.0185
-8.750 -0.5375 0.06043 0.05688 -0.0518 1.0000 0.0184
-8.500 -0.5523 0.05522 0.05156 -0.0534 1.0000 0.0183
-8.250 -0.5657 0.04987 0.04603 -0.0536 1.0000 0.0183
-8.000 -0.5767 0.04474 0.04062 -0.0525 1.0000 0.0184
-7.750 -0.5751 0.03686 0.03193 -0.0543 0.9955 0.0192
-7.500 -0.5505 0.03382 0.02867 -0.0569 0.9894 0.0200
-7.250 -0.5220 0.03128 0.02583 -0.0592 0.9843 0.0207
-7.000 -0.4948 0.02836 0.02251 -0.0609 0.9785 0.0213
-6.750 -0.4655 0.02577 0.01949 -0.0625 0.9735 0.0220
-6.500 -0.4334 0.02368 0.01701 -0.0642 0.9700 0.0231
-6.250 -0.4042 0.02214 0.01511 -0.0649 0.9639 0.0245
-6.000 -0.3727 0.02067 0.01333 -0.0660 0.9591 0.0251
-5.750 -0.3406 0.01892 0.01138 -0.0673 0.9555 0.0259
-5.500 -0.3126 0.01784 0.01022 -0.0677 0.9487 0.0268
-5.250 -0.2815 0.01696 0.00928 -0.0686 0.9439 0.0279
-5.000 -0.2495 0.01629 0.00854 -0.0696 0.9397 0.0298
-4.750 -0.2213 0.01563 0.00779 -0.0698 0.9327 0.0315
-4.500 -0.1905 0.01492 0.00699 -0.0705 0.9277 0.0328
-4.250 -0.1625 0.01415 0.00619 -0.0708 0.9214 0.0346
-4.000 -0.1338 0.01361 0.00562 -0.0711 0.9154 0.0372
-3.750 -0.1031 0.01318 0.00512 -0.0718 0.9111 0.0413
-3.500 -0.0764 0.01277 0.00471 -0.0717 0.9041 0.0478
-3.250 -0.0475 0.01238 0.00430 -0.0719 0.8987 0.0581
-3.000 -0.0194 0.01200 0.00397 -0.0721 0.8931 0.0786
-2.750 0.0075 0.01155 0.00371 -0.0722 0.8871 0.1277
-2.500 0.0335 0.01057 0.00341 -0.0726 0.8823 0.3032
-2.250 0.0570 0.00983 0.00341 -0.0721 0.8761 0.5054
-2.000 0.0830 0.00964 0.00344 -0.0715 0.8707 0.5814
-1.750 0.1101 0.00956 0.00344 -0.0711 0.8651 0.6314
-1.500 0.1353 0.00952 0.00345 -0.0701 0.8553 0.6744
-1.250 0.1600 0.00946 0.00345 -0.0689 0.8440 0.7120
-1.000 0.1855 0.00941 0.00339 -0.0679 0.8328 0.7372
-0.750 0.2122 0.00937 0.00330 -0.0673 0.8228 0.7505
-0.500 0.2386 0.00934 0.00326 -0.0668 0.8142 0.7610
-0.250 0.2659 0.00932 0.00321 -0.0664 0.8075 0.7716
0.000 0.2926 0.00931 0.00320 -0.0660 0.7996 0.7825
0.250 0.3196 0.00930 0.00317 -0.0656 0.7925 0.7937
0.500 0.3459 0.00929 0.00319 -0.0651 0.7840 0.8047
0.750 0.3727 0.00928 0.00317 -0.0646 0.7762 0.8163
1.000 0.3989 0.00928 0.00319 -0.0640 0.7668 0.8289
1.250 0.4252 0.00927 0.00320 -0.0635 0.7573 0.8420
1.500 0.4513 0.00926 0.00320 -0.0628 0.7476 0.8562
1.750 0.4770 0.00925 0.00323 -0.0621 0.7358 0.8717
2.000 0.5030 0.00923 0.00325 -0.0615 0.7234 0.8889
2.250 0.5298 0.00921 0.00326 -0.0610 0.7090 0.9094
2.500 0.5600 0.00918 0.00327 -0.0612 0.6915 0.9348
2.750 0.5965 0.00917 0.00327 -0.0630 0.6672 0.9914
3.000 0.6225 0.00929 0.00329 -0.0625 0.6320 1.0000
3.250 0.6456 0.00956 0.00327 -0.0614 0.5621 1.0000
3.500 0.6654 0.01018 0.00339 -0.0598 0.4822 1.0000
3.750 0.6876 0.01072 0.00364 -0.0589 0.4303 1.0000
4.000 0.7114 0.01116 0.00392 -0.0583 0.3962 1.0000
4.250 0.7359 0.01155 0.00421 -0.0579 0.3681 1.0000
4.500 0.7603 0.01194 0.00451 -0.0574 0.3412 1.0000
4.750 0.7849 0.01232 0.00482 -0.0569 0.3173 1.0000
5.000 0.8093 0.01272 0.00514 -0.0564 0.2916 1.0000
5.250 0.8331 0.01316 0.00550 -0.0559 0.2589 1.0000
5.500 0.8553 0.01376 0.00589 -0.0552 0.2113 1.0000
5.750 0.8759 0.01457 0.00638 -0.0544 0.1564 1.0000
6.000 0.8971 0.01535 0.00694 -0.0536 0.1193 1.0000
6.250 0.9196 0.01598 0.00750 -0.0529 0.0985 1.0000
6.500 0.9420 0.01661 0.00807 -0.0522 0.0830 1.0000
6.750 0.9644 0.01722 0.00866 -0.0516 0.0708 1.0000
7.000 0.9868 0.01783 0.00929 -0.0509 0.0615 1.0000
7.250 1.0082 0.01853 0.01001 -0.0500 0.0536 1.0000
7.500 1.0297 0.01920 0.01073 -0.0492 0.0470 1.0000
7.750 1.0499 0.02000 0.01156 -0.0482 0.0421 1.0000
8.000 1.0706 0.02071 0.01235 -0.0472 0.0380 1.0000
8.250 1.0891 0.02164 0.01329 -0.0460 0.0347 1.0000
8.500 1.1077 0.02252 0.01428 -0.0448 0.0329 1.0000
8.750 1.1260 0.02343 0.01529 -0.0436 0.0312 1.0000
9.000 1.1439 0.02433 0.01629 -0.0423 0.0295 1.0000
9.250 1.1609 0.02527 0.01728 -0.0410 0.0279 1.0000
9.500 1.1738 0.02663 0.01867 -0.0393 0.0264 1.0000
9.750 1.1898 0.02771 0.01993 -0.0378 0.0255 1.0000
10.000 1.2042 0.02885 0.02122 -0.0362 0.0245 1.0000
10.250 1.2172 0.02997 0.02247 -0.0344 0.0233 1.0000
10.500 1.2289 0.03108 0.02368 -0.0326 0.0222 1.0000
10.750 1.2390 0.03228 0.02497 -0.0307 0.0213 1.0000
11.000 1.2469 0.03388 0.02665 -0.0288 0.0206 1.0000
11.250 1.2539 0.03581 0.02871 -0.0269 0.0199 1.0000
11.500 1.2616 0.03745 0.03060 -0.0251 0.0193 1.0000
11.750 1.2672 0.03928 0.03265 -0.0234 0.0186 1.0000
12.000 1.2715 0.04110 0.03467 -0.0219 0.0178 1.0000
12.250 1.2743 0.04308 0.03682 -0.0205 0.0171 1.0000
12.500 1.2757 0.04527 0.03916 -0.0193 0.0167 1.0000
12.750 1.2755 0.04774 0.04177 -0.0183 0.0163 1.0000
13.000 1.2739 0.05042 0.04459 -0.0176 0.0159 1.0000
13.250 1.2699 0.05356 0.04786 -0.0172 0.0156 1.0000
13.500 1.2624 0.05737 0.05184 -0.0172 0.0153 1.0000
13.750 1.2525 0.06163 0.05633 -0.0177 0.0152 1.0000
14.000 1.2407 0.06635 0.06130 -0.0189 0.0150 1.0000
14.250 1.2261 0.07187 0.06708 -0.0210 0.0148 1.0000
14.500 1.2099 0.07811 0.07356 -0.0239 0.0148 1.0000
14.750 1.1916 0.08533 0.08102 -0.0280 0.0147 1.0000
15.000 1.1716 0.09350 0.08941 -0.0330 0.0147 1.0000
15.250 1.1506 0.10253 0.09864 -0.0387 0.0147 1.0000
15.500 1.1269 0.11273 0.10903 -0.0453 0.0148 1.0000
15.750 1.1012 0.12405 0.12051 -0.0526 0.0150 1.0000
16.000 1.0719 0.13715 0.13374 -0.0610 0.0152 1.0000
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