HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 200,000 Max Cl/Cd: 67.73 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3015-il-200000-n5.txt Download as CSV file: xf-hq3015-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6411 0.07194 0.06772 -0.0740 1.0000 0.0181
-13.750 -0.6840 0.06118 0.05669 -0.0811 1.0000 0.0178
-13.500 -0.7084 0.05488 0.05021 -0.0846 1.0000 0.0178
-13.250 -0.7260 0.05020 0.04536 -0.0866 1.0000 0.0179
-13.000 -0.7404 0.04641 0.04142 -0.0875 1.0000 0.0181
-12.750 -0.7530 0.04325 0.03811 -0.0875 1.0000 0.0184
-12.500 -0.7648 0.04063 0.03537 -0.0866 1.0000 0.0186
-12.250 -0.7784 0.03855 0.03318 -0.0845 1.0000 0.0188
-12.000 -0.7829 0.03624 0.03069 -0.0841 0.9961 0.0192
-11.750 -0.7685 0.03364 0.02784 -0.0869 0.9857 0.0199
-11.500 -0.7494 0.03195 0.02606 -0.0893 0.9770 0.0205
-11.250 -0.7266 0.03048 0.02445 -0.0915 0.9701 0.0214
-11.000 -0.7067 0.02901 0.02280 -0.0925 0.9611 0.0227
-10.750 -0.6817 0.02740 0.02094 -0.0941 0.9552 0.0243
-10.500 -0.6604 0.02650 0.02000 -0.0946 0.9460 0.0255
-10.250 -0.6331 0.02555 0.01891 -0.0959 0.9403 0.0276
-10.000 -0.6117 0.02461 0.01779 -0.0959 0.9316 0.0298
-9.750 -0.5853 0.02388 0.01701 -0.0968 0.9256 0.0316
-9.500 -0.5628 0.02318 0.01619 -0.0966 0.9176 0.0338
-9.250 -0.5378 0.02237 0.01521 -0.0968 0.9115 0.0360
-9.000 -0.5150 0.02184 0.01465 -0.0967 0.9045 0.0380
-8.750 -0.4910 0.02136 0.01406 -0.0965 0.8977 0.0407
-8.500 -0.4665 0.02082 0.01337 -0.0963 0.8917 0.0433
-8.250 -0.4450 0.02035 0.01290 -0.0957 0.8843 0.0459
-8.000 -0.4202 0.01991 0.01236 -0.0955 0.8788 0.0487
-7.750 -0.3974 0.01947 0.01180 -0.0949 0.8719 0.0511
-7.500 -0.3751 0.01882 0.01110 -0.0943 0.8657 0.0534
-7.250 -0.3515 0.01832 0.01056 -0.0938 0.8604 0.0559
-7.000 -0.3288 0.01788 0.01007 -0.0931 0.8539 0.0585
-6.750 -0.3046 0.01742 0.00950 -0.0926 0.8485 0.0609
-6.500 -0.2816 0.01693 0.00896 -0.0920 0.8429 0.0637
-6.250 -0.2586 0.01648 0.00851 -0.0914 0.8368 0.0673
-6.000 -0.2337 0.01609 0.00804 -0.0910 0.8319 0.0711
-5.750 -0.2097 0.01573 0.00762 -0.0905 0.8262 0.0751
-5.500 -0.1858 0.01532 0.00722 -0.0900 0.8204 0.0806
-5.000 -0.1357 0.01466 0.00651 -0.0893 0.8102 0.0968
-4.750 -0.1109 0.01432 0.00619 -0.0889 0.8046 0.1094
-4.500 -0.0852 0.01397 0.00586 -0.0887 0.8002 0.1282
-4.250 -0.0608 0.01359 0.00561 -0.0883 0.7948 0.1586
-4.000 -0.0364 0.01318 0.00536 -0.0880 0.7892 0.2036
-3.750 -0.0113 0.01274 0.00509 -0.0878 0.7847 0.2586
-3.500 0.0125 0.01225 0.00485 -0.0874 0.7795 0.3232
-3.250 0.0349 0.01175 0.00480 -0.0867 0.7738 0.4371
-3.000 0.0614 0.01162 0.00477 -0.0863 0.7693 0.4922
-2.750 0.0881 0.01159 0.00476 -0.0860 0.7641 0.5243
-2.500 0.1146 0.01158 0.00477 -0.0856 0.7583 0.5494
-2.250 0.1423 0.01158 0.00474 -0.0853 0.7535 0.5725
-2.000 0.1691 0.01162 0.00478 -0.0849 0.7479 0.5939
-1.750 0.1955 0.01167 0.00484 -0.0844 0.7419 0.6135
-1.500 0.2235 0.01169 0.00480 -0.0843 0.7370 0.6265
-1.250 0.2506 0.01172 0.00481 -0.0840 0.7313 0.6359
-1.000 0.2778 0.01174 0.00481 -0.0838 0.7255 0.6443
-0.750 0.3062 0.01175 0.00475 -0.0838 0.7208 0.6534
-0.500 0.3327 0.01179 0.00481 -0.0834 0.7148 0.6620
-0.250 0.3601 0.01183 0.00481 -0.0832 0.7090 0.6720
0.000 0.3881 0.01184 0.00479 -0.0831 0.7041 0.6785
0.250 0.4144 0.01186 0.00481 -0.0827 0.6959 0.6849
0.500 0.4426 0.01184 0.00471 -0.0826 0.6886 0.6903
0.750 0.4683 0.01184 0.00473 -0.0821 0.6783 0.6951
1.000 0.4955 0.01185 0.00469 -0.0819 0.6699 0.7012
1.250 0.5222 0.01188 0.00471 -0.0817 0.6620 0.7070
1.500 0.5493 0.01191 0.00474 -0.0814 0.6551 0.7126
1.750 0.5758 0.01195 0.00478 -0.0811 0.6468 0.7190
2.000 0.6025 0.01199 0.00482 -0.0808 0.6390 0.7245
2.250 0.6285 0.01204 0.00489 -0.0804 0.6301 0.7309
2.500 0.6548 0.01210 0.00493 -0.0801 0.6210 0.7378
2.750 0.6806 0.01214 0.00498 -0.0796 0.6112 0.7436
3.000 0.7057 0.01221 0.00506 -0.0791 0.5994 0.7508
3.250 0.7305 0.01227 0.00513 -0.0784 0.5866 0.7574
3.500 0.7550 0.01235 0.00520 -0.0777 0.5729 0.7648
3.750 0.7793 0.01245 0.00530 -0.0770 0.5590 0.7720
4.000 0.8030 0.01256 0.00540 -0.0762 0.5445 0.7796
4.250 0.8265 0.01269 0.00552 -0.0754 0.5288 0.7878
4.500 0.8491 0.01284 0.00566 -0.0744 0.5114 0.7964
4.750 0.8708 0.01302 0.00581 -0.0732 0.4934 0.8051
5.000 0.8916 0.01323 0.00598 -0.0719 0.4744 0.8151
5.500 0.9300 0.01373 0.00641 -0.0688 0.4341 0.8378
5.750 0.9484 0.01402 0.00667 -0.0671 0.4139 0.8519
6.000 0.9660 0.01432 0.00695 -0.0654 0.3943 0.8701
6.250 0.9850 0.01462 0.00727 -0.0639 0.3748 0.9002
6.500 1.0122 0.01500 0.00764 -0.0644 0.3530 1.0000
6.750 1.0286 0.01546 0.00801 -0.0627 0.3356 1.0000
7.000 1.0433 0.01592 0.00841 -0.0607 0.3202 1.0000
7.250 1.0576 0.01643 0.00885 -0.0586 0.3061 1.0000
7.500 1.0719 0.01696 0.00932 -0.0567 0.2933 1.0000
7.750 1.0860 0.01753 0.00984 -0.0548 0.2818 1.0000
8.000 1.1010 0.01808 0.01038 -0.0530 0.2707 1.0000
8.250 1.1160 0.01866 0.01094 -0.0514 0.2598 1.0000
8.500 1.1298 0.01929 0.01155 -0.0496 0.2495 1.0000
8.750 1.1442 0.01993 0.01218 -0.0480 0.2393 1.0000
9.000 1.1586 0.02058 0.01284 -0.0465 0.2289 1.0000
9.250 1.1716 0.02132 0.01356 -0.0448 0.2195 1.0000
9.500 1.1854 0.02204 0.01430 -0.0433 0.2100 1.0000
9.750 1.1988 0.02281 0.01508 -0.0419 0.2013 1.0000
10.000 1.2102 0.02371 0.01595 -0.0403 0.1925 1.0000
10.250 1.2238 0.02452 0.01681 -0.0389 0.1841 1.0000
10.500 1.2342 0.02553 0.01780 -0.0374 0.1765 1.0000
10.750 1.2472 0.02642 0.01874 -0.0362 0.1686 1.0000
11.000 1.2570 0.02753 0.01984 -0.0347 0.1616 1.0000
11.250 1.2696 0.02850 0.02087 -0.0336 0.1545 1.0000
11.500 1.2779 0.02977 0.02214 -0.0322 0.1482 1.0000
11.750 1.2906 0.03079 0.02325 -0.0312 0.1416 1.0000
12.000 1.2991 0.03211 0.02458 -0.0300 0.1356 1.0000
12.250 1.3096 0.03333 0.02587 -0.0289 0.1293 1.0000
12.500 1.3173 0.03478 0.02734 -0.0279 0.1225 1.0000
12.750 1.3260 0.03619 0.02881 -0.0269 0.1160 1.0000
13.000 1.3316 0.03789 0.03051 -0.0259 0.1086 1.0000
13.250 1.3397 0.03944 0.03214 -0.0251 0.1028 1.0000
13.500 1.3439 0.04136 0.03406 -0.0243 0.0957 1.0000
13.750 1.3506 0.04312 0.03589 -0.0236 0.0900 1.0000
14.000 1.3545 0.04519 0.03799 -0.0230 0.0842 1.0000
14.250 1.3592 0.04725 0.04012 -0.0225 0.0799 1.0000
14.500 1.3634 0.04941 0.04235 -0.0221 0.0749 1.0000
14.750 1.3642 0.05200 0.04497 -0.0218 0.0704 1.0000
15.000 1.3686 0.05428 0.04737 -0.0216 0.0673 1.0000
15.250 1.3704 0.05691 0.05008 -0.0215 0.0637 1.0000
15.500 1.3688 0.06001 0.05322 -0.0216 0.0604 1.0000
15.750 1.3707 0.06277 0.05609 -0.0218 0.0571 1.0000
16.000 1.3702 0.06592 0.05933 -0.0222 0.0539 1.0000
16.250 1.3672 0.06948 0.06296 -0.0228 0.0514 1.0000
16.500 1.3652 0.07300 0.06658 -0.0235 0.0490 1.0000
16.750 1.3640 0.07649 0.07020 -0.0243 0.0469 1.0000
17.000 1.3607 0.08038 0.07421 -0.0253 0.0450 1.0000
17.250 1.3557 0.08462 0.07855 -0.0266 0.0434 1.0000
17.500 1.3490 0.08920 0.08325 -0.0282 0.0422 1.0000
17.750 1.3439 0.09364 0.08782 -0.0298 0.0408 1.0000
18.000 1.3393 0.09809 0.09241 -0.0315 0.0394 1.0000
18.250 1.3330 0.10289 0.09735 -0.0334 0.0380 1.0000
18.500 1.3253 0.10801 0.10259 -0.0357 0.0367 1.0000
18.750 1.3156 0.11356 0.10825 -0.0383 0.0355 1.0000
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