HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Reynolds number: 50,000 Max Cl/Cd: 15.1 at α=11.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq300gd2-il-50000-n5.txt Download as CSV file: xf-hq300gd2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3028 0.12270 0.11613 -0.0570 1.0000 0.0711
-11.250 -0.3020 0.12058 0.11411 -0.0550 1.0000 0.0687
-10.750 -0.3294 0.11138 0.10508 -0.0604 0.9913 0.0602
-10.500 -0.3189 0.10607 0.09977 -0.0651 0.9833 0.0598
-10.250 -0.3114 0.10049 0.09418 -0.0702 0.9743 0.0595
-10.000 -0.3048 0.09443 0.08810 -0.0761 0.9662 0.0591
-9.750 -0.3015 0.08784 0.08147 -0.0827 0.9575 0.0584
-9.500 -0.3054 0.08175 0.07533 -0.0886 0.9467 0.0576
-9.250 -0.3140 0.07624 0.06970 -0.0935 0.9356 0.0568
-9.000 -0.3247 0.07145 0.06475 -0.0969 0.9241 0.0561
-8.750 -0.3351 0.06748 0.06057 -0.0984 0.9117 0.0556
-8.500 -0.3408 0.06369 0.05651 -0.0993 0.9013 0.0551
-8.250 -0.3396 0.05987 0.05233 -0.1002 0.8931 0.0548
-8.000 -0.3389 0.05685 0.04897 -0.0996 0.8833 0.0547
-7.750 -0.3276 0.05357 0.04526 -0.1002 0.8767 0.0551
-7.500 -0.3194 0.05121 0.04253 -0.0994 0.8682 0.0563
-7.250 -0.3031 0.04858 0.03940 -0.0995 0.8618 0.0582
-7.000 -0.2859 0.04624 0.03652 -0.0992 0.8555 0.0595
-6.750 -0.2677 0.04421 0.03402 -0.0986 0.8484 0.0603
-6.500 -0.2411 0.04194 0.03146 -0.0991 0.8441 0.0615
-6.250 -0.2218 0.04062 0.03005 -0.0984 0.8375 0.0638
-6.000 -0.1985 0.03939 0.02861 -0.0981 0.8317 0.0671
-5.750 -0.1685 0.03795 0.02682 -0.0983 0.8278 0.0702
-5.500 -0.1464 0.03705 0.02564 -0.0970 0.8218 0.0721
-5.250 -0.1240 0.03609 0.02475 -0.0960 0.8162 0.0755
-5.000 -0.0957 0.03529 0.02384 -0.0956 0.8123 0.0814
-4.750 -0.0707 0.03470 0.02306 -0.0946 0.8078 0.0862
-4.500 -0.0554 0.03428 0.02269 -0.0927 0.8011 0.0906
-4.250 -0.0311 0.03372 0.02197 -0.0921 0.7968 0.0999
-4.000 -0.0050 0.03285 0.02110 -0.0921 0.7936 0.1125
-3.750 0.0037 0.03272 0.02106 -0.0900 0.7858 0.1259
-3.500 0.0240 0.03167 0.02040 -0.0898 0.7812 0.1702
-3.250 0.0290 0.02987 0.02090 -0.0852 0.7779 0.5264
-3.000 0.0245 0.03159 0.02299 -0.0762 0.7704 0.6757
-2.750 0.0374 0.03296 0.02414 -0.0716 0.7655 0.7536
-2.500 0.0522 0.03416 0.02515 -0.0658 0.7622 0.8057
-2.250 0.0532 0.03525 0.02617 -0.0591 0.7555 0.8434
-2.000 0.0733 0.03564 0.02636 -0.0559 0.7510 0.8771
-1.750 0.1020 0.03553 0.02597 -0.0559 0.7476 0.8915
-1.500 0.1346 0.03531 0.02549 -0.0568 0.7450 0.9028
-1.250 0.1350 0.03590 0.02601 -0.0536 0.7365 0.9158
-1.000 0.1628 0.03586 0.02575 -0.0541 0.7326 0.9267
-0.750 0.2015 0.03568 0.02535 -0.0564 0.7299 0.9356
-0.500 0.2156 0.03624 0.02582 -0.0557 0.7229 0.9455
-0.250 0.2435 0.03643 0.02585 -0.0568 0.7180 0.9534
0.000 0.2815 0.03640 0.02565 -0.0592 0.7148 0.9595
0.250 0.3095 0.03675 0.02589 -0.0606 0.7100 0.9656
0.500 0.3268 0.03745 0.02652 -0.0607 0.7029 0.9727
0.750 0.3661 0.03755 0.02650 -0.0635 0.6994 0.9765
1.000 0.4075 0.03749 0.02631 -0.0664 0.6969 0.9800
1.250 0.4129 0.03889 0.02772 -0.0655 0.6872 0.9874
1.500 0.4470 0.03906 0.02782 -0.0673 0.6834 0.9915
1.750 0.4864 0.03896 0.02763 -0.0696 0.6808 0.9949
2.000 0.4659 0.04066 0.02938 -0.0645 0.6693 1.0000
2.250 0.4892 0.04065 0.02930 -0.0639 0.6659 1.0000
2.500 0.4549 0.04213 0.03081 -0.0562 0.6546 1.0000
2.750 0.4781 0.04224 0.03087 -0.0558 0.6506 1.0000
3.000 0.4696 0.04358 0.03222 -0.0523 0.6409 1.0000
3.250 0.4942 0.04389 0.03250 -0.0524 0.6360 1.0000
3.500 0.5248 0.04400 0.03257 -0.0531 0.6323 1.0000
3.750 0.5251 0.04560 0.03421 -0.0515 0.6216 1.0000
4.000 0.5594 0.04561 0.03420 -0.0525 0.6181 1.0000
4.250 0.5626 0.04734 0.03598 -0.0516 0.6072 1.0000
4.500 0.5960 0.04742 0.03605 -0.0526 0.6031 1.0000
4.750 0.6033 0.04909 0.03777 -0.0521 0.5926 1.0000
5.000 0.6356 0.04922 0.03794 -0.0531 0.5880 1.0000
5.500 0.6768 0.05102 0.03982 -0.0537 0.5726 1.0000
6.000 0.7187 0.05280 0.04174 -0.0544 0.5569 1.0000
6.250 0.7278 0.05460 0.04362 -0.0543 0.5459 1.0000
6.500 0.7610 0.05454 0.04362 -0.0550 0.5411 1.0000
6.750 0.7686 0.05650 0.04567 -0.0549 0.5294 1.0000
7.000 0.8034 0.05623 0.04550 -0.0556 0.5252 1.0000
7.250 0.8094 0.05837 0.04773 -0.0554 0.5129 1.0000
7.500 0.8458 0.05784 0.04730 -0.0560 0.5091 1.0000
8.000 0.8597 0.06209 0.05177 -0.0558 0.4852 1.0000
8.250 0.8912 0.06186 0.05165 -0.0562 0.4800 1.0000
8.500 0.8972 0.06413 0.05403 -0.0561 0.4677 1.0000
8.750 0.9326 0.06336 0.05341 -0.0563 0.4637 1.0000
9.000 0.9361 0.06593 0.05609 -0.0563 0.4509 1.0000
9.500 0.9755 0.06752 0.05793 -0.0562 0.4344 1.0000
9.750 0.9794 0.07016 0.06071 -0.0562 0.4221 1.0000
10.000 1.0154 0.06886 0.05956 -0.0560 0.4182 1.0000
10.250 1.0164 0.07186 0.06268 -0.0560 0.4053 1.0000
10.750 1.0544 0.07330 0.06442 -0.0557 0.3889 1.0000
11.250 1.0937 0.07444 0.06586 -0.0552 0.3726 1.0000
11.750 1.1350 0.07519 0.06692 -0.0545 0.3563 1.0000
12.000 1.1280 0.07930 0.07117 -0.0547 0.3432 1.0000
12.250 1.1227 0.08334 0.07533 -0.0550 0.3310 1.0000
12.500 1.1694 0.07987 0.07204 -0.0539 0.3266 1.0000
12.750 1.1571 0.08486 0.07715 -0.0543 0.3138 1.0000
13.250 1.1981 0.08528 0.07789 -0.0534 0.2967 1.0000
13.500 1.1799 0.09135 0.08409 -0.0543 0.2842 1.0000
13.750 1.1785 0.09493 0.08779 -0.0548 0.2738 1.0000
14.000 1.2215 0.09137 0.08439 -0.0532 0.2664 1.0000
14.250 1.1960 0.09881 0.09195 -0.0548 0.2544 1.0000
14.500 1.1957 0.10226 0.09552 -0.0554 0.2442 1.0000
14.750 1.2517 0.09609 0.08946 -0.0528 0.2351 1.0000
15.000 1.2121 0.10611 0.09964 -0.0558 0.2240 1.0000
15.250 1.2007 0.11158 0.10523 -0.0574 0.2135 1.0000
15.500 1.2251 0.11040 0.10414 -0.0565 0.2028 1.0000
15.750 1.2446 0.11004 0.10380 -0.0560 0.1907 1.0000
16.000 1.2182 0.11847 0.11241 -0.0592 0.1809 1.0000
16.250 1.2118 0.12324 0.11727 -0.0611 0.1704 1.0000
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Polar data table (+)
Polar graphs
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