HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 200,000 Max Cl/Cd: 83.55 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3010-il-200000.txt Download as CSV file: xf-hq3010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3847 0.08989 0.08664 -0.0463 1.0000 0.0386
-8.250 -0.4024 0.08780 0.08465 -0.0448 1.0000 0.0386
-8.000 -0.4235 0.08607 0.08301 -0.0428 1.0000 0.0386
-7.750 -0.4409 0.08363 0.08058 -0.0425 1.0000 0.0387
-7.500 -0.4545 0.08115 0.07809 -0.0416 1.0000 0.0387
-7.250 -0.4680 0.07553 0.07261 -0.0392 1.0000 0.0396
-7.000 -0.4511 0.07201 0.06910 -0.0404 0.9970 0.0407
-6.750 -0.4292 0.06755 0.06460 -0.0455 0.9927 0.0423
-6.500 -0.4063 0.06210 0.05903 -0.0528 0.9867 0.0441
-6.250 -0.3768 0.05589 0.05258 -0.0617 0.9819 0.0474
-6.000 -0.3496 0.04911 0.04499 -0.0705 0.9729 0.0518
-5.750 -0.3233 0.04426 0.04024 -0.0735 0.9702 0.0538
-5.500 -0.2981 0.04166 0.03757 -0.0753 0.9649 0.0580
-5.250 -0.2679 0.03769 0.03315 -0.0789 0.9595 0.0675
-5.000 -0.2270 0.02939 0.02378 -0.0806 0.9567 0.0370
-4.750 -0.1958 0.02506 0.01890 -0.0820 0.9529 0.0332
-4.500 -0.1655 0.02206 0.01534 -0.0822 0.9477 0.0318
-4.250 -0.1290 0.02006 0.01302 -0.0836 0.9447 0.0329
-4.000 -0.0899 0.01871 0.01145 -0.0856 0.9425 0.0365
-3.750 -0.0590 0.01738 0.01005 -0.0862 0.9378 0.0424
-3.500 -0.0267 0.01628 0.00888 -0.0869 0.9330 0.0527
-3.250 0.0115 0.01541 0.00804 -0.0892 0.9301 0.0764
-3.000 0.0504 0.01468 0.00738 -0.0916 0.9277 0.1006
-2.750 0.0759 0.01411 0.00689 -0.0914 0.9204 0.1266
-2.500 0.1038 0.01210 0.00652 -0.0925 0.9163 0.5252
-2.250 0.1379 0.01190 0.00652 -0.0931 0.9134 0.6412
-2.000 0.1604 0.01197 0.00661 -0.0916 0.9050 0.6840
-1.750 0.1929 0.01190 0.00654 -0.0918 0.9009 0.7201
-1.500 0.2178 0.01193 0.00655 -0.0907 0.8935 0.7471
-1.250 0.2461 0.01185 0.00648 -0.0900 0.8880 0.7754
-1.000 0.2680 0.01182 0.00651 -0.0879 0.8809 0.8085
-0.750 0.2917 0.01168 0.00640 -0.0862 0.8743 0.8353
-0.500 0.3174 0.01156 0.00625 -0.0854 0.8678 0.8515
-0.250 0.3436 0.01142 0.00609 -0.0848 0.8608 0.8650
0.000 0.3704 0.01127 0.00593 -0.0842 0.8547 0.8798
0.250 0.3957 0.01111 0.00577 -0.0833 0.8468 0.8970
0.500 0.4235 0.01090 0.00556 -0.0828 0.8384 0.9164
0.750 0.4590 0.01060 0.00524 -0.0838 0.8306 0.9409
1.000 0.5021 0.01044 0.00508 -0.0869 0.8214 0.9748
1.250 0.5385 0.01032 0.00490 -0.0888 0.8142 1.0000
1.500 0.5660 0.01032 0.00484 -0.0889 0.8043 1.0000
1.750 0.5939 0.01031 0.00478 -0.0890 0.7941 1.0000
2.000 0.6223 0.01026 0.00469 -0.0890 0.7838 1.0000
2.250 0.6507 0.01020 0.00456 -0.0888 0.7727 1.0000
2.500 0.6781 0.01018 0.00450 -0.0885 0.7603 1.0000
2.750 0.7050 0.01020 0.00448 -0.0882 0.7472 1.0000
3.000 0.7317 0.01023 0.00451 -0.0878 0.7336 1.0000
3.250 0.7585 0.01026 0.00452 -0.0873 0.7192 1.0000
3.500 0.7850 0.01031 0.00454 -0.0869 0.7036 1.0000
3.750 0.8105 0.01038 0.00461 -0.0862 0.6850 1.0000
4.000 0.8363 0.01047 0.00470 -0.0856 0.6655 1.0000
4.250 0.8615 0.01058 0.00478 -0.0849 0.6434 1.0000
4.500 0.8863 0.01073 0.00488 -0.0841 0.6185 1.0000
4.750 0.9102 0.01092 0.00502 -0.0832 0.5888 1.0000
5.000 0.9332 0.01117 0.00520 -0.0822 0.5537 1.0000
5.250 0.9551 0.01154 0.00542 -0.0809 0.5133 1.0000
5.500 0.9755 0.01203 0.00572 -0.0796 0.4695 1.0000
5.750 0.9950 0.01262 0.00611 -0.0781 0.4255 1.0000
6.000 1.0141 0.01326 0.00656 -0.0767 0.3835 1.0000
6.250 1.0332 0.01392 0.00708 -0.0753 0.3440 1.0000
6.500 1.0519 0.01461 0.00760 -0.0739 0.3091 1.0000
6.750 1.0711 0.01528 0.00816 -0.0727 0.2790 1.0000
7.000 1.0903 0.01596 0.00875 -0.0714 0.2529 1.0000
7.250 1.1096 0.01661 0.00934 -0.0702 0.2290 1.0000
7.500 1.1290 0.01724 0.00994 -0.0691 0.2057 1.0000
7.750 1.1473 0.01792 0.01058 -0.0678 0.1808 1.0000
8.000 1.1647 0.01864 0.01121 -0.0664 0.1540 1.0000
8.250 1.1816 0.01942 0.01190 -0.0650 0.1294 1.0000
8.500 1.1975 0.02029 0.01269 -0.0635 0.1071 1.0000
8.750 1.2128 0.02120 0.01355 -0.0618 0.0872 1.0000
9.000 1.2263 0.02216 0.01445 -0.0599 0.0714 1.0000
9.250 1.2383 0.02315 0.01545 -0.0577 0.0601 1.0000
9.500 1.2487 0.02426 0.01656 -0.0554 0.0479 1.0000
9.750 1.2520 0.02596 0.01823 -0.0523 0.0337 1.0000
10.000 1.2540 0.02783 0.02013 -0.0491 0.0235 1.0000
10.250 1.2603 0.02933 0.02175 -0.0467 0.0199 1.0000
10.500 1.2612 0.03129 0.02379 -0.0439 0.0179 1.0000
10.750 1.2571 0.03389 0.02649 -0.0410 0.0169 1.0000
11.000 1.2634 0.03570 0.02847 -0.0391 0.0161 1.0000
11.250 1.2683 0.03781 0.03074 -0.0372 0.0155 1.0000
11.500 1.2731 0.04005 0.03315 -0.0355 0.0149 1.0000
11.750 1.2775 0.04248 0.03575 -0.0339 0.0143 1.0000
12.000 1.2815 0.04505 0.03851 -0.0325 0.0140 1.0000
12.250 1.2842 0.04784 0.04149 -0.0311 0.0137 1.0000
12.500 1.2851 0.05091 0.04478 -0.0300 0.0135 1.0000
12.750 1.2834 0.05430 0.04841 -0.0290 0.0134 1.0000
13.000 1.2786 0.05804 0.05240 -0.0283 0.0133 1.0000
13.250 1.2708 0.06224 0.05687 -0.0281 0.0133 1.0000
13.500 1.2600 0.06689 0.06178 -0.0283 0.0133 1.0000
13.750 1.2466 0.07207 0.06723 -0.0292 0.0134 1.0000
14.000 1.2304 0.07786 0.07328 -0.0308 0.0135 1.0000
14.250 1.2119 0.08439 0.08006 -0.0333 0.0136 1.0000
14.500 1.1925 0.09158 0.08749 -0.0368 0.0138 1.0000
14.750 1.1717 0.09964 0.09579 -0.0413 0.0140 1.0000
15.000 1.1498 0.10861 0.10497 -0.0468 0.0141 1.0000
15.250 1.1275 0.11844 0.11500 -0.0532 0.0143 1.0000
15.500 1.1042 0.12941 0.12614 -0.0605 0.0146 1.0000
15.750 1.0778 0.14219 0.13907 -0.0690 0.0149 1.0000
16.000 1.0470 0.15765 0.15462 -0.0787 0.0155 1.0000
16.250 1.0210 0.17272 0.16968 -0.0872 0.0163 1.0000
16.500 1.0094 0.18282 0.17974 -0.0923 0.0169 1.0000
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