HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Reynolds number: 200,000 Max Cl/Cd: 74.71 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq300gd2-il-200000.txt Download as CSV file: xf-hq300gd2-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1404 0.09466 0.09130 -0.0775 0.8908 0.0583
-10.750 -0.1667 0.08765 0.08432 -0.0843 0.8846 0.0602
-10.500 -0.1960 0.07918 0.07582 -0.0919 0.8790 0.0605
-10.250 -0.1767 0.07718 0.07383 -0.0868 0.8707 0.0618
-10.000 -0.1614 0.07598 0.07258 -0.0841 0.8624 0.0631
-9.750 -0.2896 0.07521 0.07165 -0.0960 0.8818 0.0601
-9.500 -0.3195 0.07136 0.06758 -0.0987 0.8696 0.0603
-9.250 -0.3405 0.06856 0.06441 -0.1004 0.8598 0.0605
-9.000 -0.3269 0.06167 0.05770 -0.1009 0.8535 0.0620
-8.750 -0.3116 0.05911 0.05517 -0.1006 0.8467 0.0633
-8.500 -0.3050 0.05644 0.05240 -0.1008 0.8403 0.0649
-8.250 -0.3006 0.05348 0.04927 -0.1016 0.8327 0.0675
-8.000 -0.3109 0.05009 0.04508 -0.1026 0.8264 0.0733
-7.750 -0.2919 0.04654 0.04169 -0.1029 0.8199 0.0751
-7.500 -0.2743 0.04427 0.03934 -0.1029 0.8142 0.0780
-7.250 -0.2626 0.04187 0.03639 -0.1034 0.8096 0.0876
-7.000 -0.2410 0.03315 0.02627 -0.1018 0.8042 0.0509
-6.750 -0.2173 0.02994 0.02295 -0.1017 0.7991 0.0485
-6.500 -0.1924 0.02752 0.02017 -0.1015 0.7949 0.0476
-6.250 -0.1659 0.02609 0.01843 -0.1014 0.7897 0.0490
-6.000 -0.1387 0.02499 0.01702 -0.1014 0.7845 0.0500
-5.750 -0.1116 0.02361 0.01541 -0.1012 0.7804 0.0506
-5.500 -0.0861 0.02187 0.01359 -0.1007 0.7771 0.0520
-5.250 -0.0602 0.02112 0.01289 -0.1007 0.7716 0.0548
-5.000 -0.0335 0.02041 0.01212 -0.1005 0.7669 0.0573
-4.750 -0.0065 0.01972 0.01132 -0.1002 0.7632 0.0592
-4.500 0.0195 0.01896 0.01054 -0.0999 0.7596 0.0618
-4.250 0.0453 0.01835 0.01004 -0.1000 0.7548 0.0665
-4.000 0.0729 0.01789 0.00953 -0.1002 0.7506 0.0712
-3.750 0.1012 0.01715 0.00882 -0.1009 0.7471 0.0787
-3.500 0.1311 0.01661 0.00828 -0.1018 0.7436 0.0957
-3.250 0.1640 0.01384 0.00798 -0.1058 0.7391 0.6065
-3.000 0.1810 0.01454 0.00890 -0.1020 0.7351 0.7089
-2.750 0.2041 0.01528 0.00954 -0.0999 0.7317 0.7451
-2.500 0.2209 0.01617 0.01035 -0.0958 0.7289 0.7641
-2.250 0.2353 0.01707 0.01128 -0.0917 0.7240 0.7807
-2.000 0.2510 0.01780 0.01197 -0.0878 0.7200 0.7959
-1.750 0.2682 0.01834 0.01244 -0.0843 0.7166 0.8106
-1.500 0.2866 0.01876 0.01278 -0.0811 0.7138 0.8253
-1.250 0.3030 0.01903 0.01303 -0.0779 0.7099 0.8342
-1.000 0.3277 0.01914 0.01309 -0.0776 0.7055 0.8421
-0.750 0.3503 0.01914 0.01302 -0.0763 0.7019 0.8481
-0.500 0.3798 0.01914 0.01291 -0.0770 0.6989 0.8559
-0.250 0.4016 0.01909 0.01279 -0.0753 0.6961 0.8613
0.000 0.4263 0.01930 0.01301 -0.0755 0.6911 0.8694
0.250 0.4463 0.01921 0.01290 -0.0737 0.6871 0.8751
0.500 0.4731 0.01917 0.01279 -0.0736 0.6840 0.8819
0.750 0.4998 0.01906 0.01259 -0.0734 0.6813 0.8873
1.000 0.5206 0.01915 0.01271 -0.0725 0.6766 0.8926
1.250 0.5479 0.01926 0.01280 -0.0731 0.6721 0.8976
1.500 0.5735 0.01907 0.01257 -0.0727 0.6685 0.9014
1.750 0.6018 0.01891 0.01234 -0.0729 0.6657 0.9050
2.000 0.6260 0.01907 0.01253 -0.0729 0.6606 0.9091
2.250 0.6543 0.01914 0.01260 -0.0737 0.6556 0.9125
2.500 0.6806 0.01890 0.01231 -0.0734 0.6520 0.9155
2.750 0.7111 0.01874 0.01208 -0.0740 0.6490 0.9183
3.000 0.7331 0.01895 0.01239 -0.0738 0.6427 0.9219
3.250 0.7634 0.01893 0.01235 -0.0747 0.6381 0.9247
3.500 0.7938 0.01872 0.01210 -0.0754 0.6346 0.9269
3.750 0.8172 0.01875 0.01217 -0.0749 0.6296 0.9300
4.000 0.8427 0.01877 0.01224 -0.0750 0.6240 0.9329
4.250 0.8745 0.01864 0.01208 -0.0760 0.6199 0.9350
4.500 0.9057 0.01864 0.01207 -0.0771 0.6157 0.9375
4.750 0.9273 0.01870 0.01223 -0.0765 0.6091 0.9403
5.000 0.9570 0.01852 0.01204 -0.0770 0.6046 0.9425
5.250 0.9872 0.01843 0.01195 -0.0777 0.6001 0.9447
5.500 1.0107 0.01855 0.01217 -0.0776 0.5929 0.9476
5.750 1.0431 0.01838 0.01199 -0.0787 0.5880 0.9499
6.000 1.0679 0.01839 0.01208 -0.0786 0.5815 0.9522
6.250 1.0945 0.01828 0.01202 -0.0787 0.5748 0.9545
6.500 1.1261 0.01809 0.01180 -0.0795 0.5694 0.9568
6.750 1.1478 0.01817 0.01201 -0.0790 0.5607 0.9600
7.000 1.1816 0.01794 0.01173 -0.0802 0.5548 0.9621
7.250 1.2006 0.01800 0.01195 -0.0792 0.5451 0.9649
7.500 1.2295 0.01786 0.01182 -0.0796 0.5375 0.9673
7.750 1.2527 0.01786 0.01192 -0.0793 0.5276 0.9704
8.000 1.2763 0.01790 0.01203 -0.0790 0.5175 0.9738
8.250 1.3031 0.01779 0.01193 -0.0791 0.5078 0.9770
8.500 1.3243 0.01790 0.01214 -0.0786 0.4955 0.9807
8.750 1.3455 0.01808 0.01240 -0.0781 0.4825 0.9846
9.000 1.3672 0.01830 0.01267 -0.0777 0.4686 0.9898
9.250 1.3864 0.01857 0.01300 -0.0770 0.4538 1.0000
9.500 1.4035 0.01903 0.01347 -0.0760 0.4384 1.0000
9.750 1.4194 0.01964 0.01409 -0.0751 0.4223 1.0000
10.000 1.4343 0.02041 0.01485 -0.0741 0.4059 1.0000
10.250 1.4476 0.02135 0.01577 -0.0732 0.3893 1.0000
10.500 1.4594 0.02244 0.01684 -0.0722 0.3728 1.0000
10.750 1.4686 0.02375 0.01811 -0.0711 0.3557 1.0000
11.000 1.4754 0.02529 0.01966 -0.0701 0.3377 1.0000
11.250 1.4807 0.02703 0.02139 -0.0691 0.3199 1.0000
11.500 1.4853 0.02892 0.02327 -0.0682 0.3029 1.0000
11.750 1.4898 0.03090 0.02527 -0.0675 0.2872 1.0000
12.000 1.4941 0.03297 0.02735 -0.0668 0.2725 1.0000
12.250 1.4979 0.03515 0.02954 -0.0662 0.2584 1.0000
12.500 1.5009 0.03744 0.03185 -0.0657 0.2449 1.0000
12.750 1.5029 0.03985 0.03428 -0.0651 0.2317 1.0000
13.000 1.5039 0.04243 0.03687 -0.0647 0.2187 1.0000
13.250 1.5039 0.04519 0.03963 -0.0643 0.2057 1.0000
13.500 1.5043 0.04801 0.04249 -0.0641 0.1923 1.0000
13.750 1.5040 0.05099 0.04551 -0.0639 0.1790 1.0000
14.000 1.5025 0.05415 0.04870 -0.0638 0.1656 1.0000
14.250 1.4994 0.05754 0.05210 -0.0638 0.1520 1.0000
14.500 1.4950 0.06117 0.05573 -0.0638 0.1382 1.0000
14.750 1.4885 0.06512 0.05966 -0.0639 0.1240 1.0000
15.000 1.4794 0.06943 0.06393 -0.0641 0.1096 1.0000
15.250 1.4699 0.07391 0.06840 -0.0644 0.0939 1.0000
15.500 1.4574 0.07884 0.07329 -0.0648 0.0799 1.0000
15.750 1.4441 0.08396 0.07838 -0.0653 0.0689 1.0000
16.000 1.4308 0.08919 0.08359 -0.0660 0.0607 1.0000
16.250 1.4182 0.09445 0.08884 -0.0669 0.0547 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il)