HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 200,000 Max Cl/Cd: 77.31 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3010-il-200000-n5.txt Download as CSV file: xf-hq3010-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3701 0.09569 0.09213 -0.0395 1.0000 0.0129
-9.250 -0.3699 0.09240 0.08887 -0.0401 1.0000 0.0126
-9.000 -0.3715 0.08897 0.08550 -0.0408 1.0000 0.0124
-8.750 -0.3745 0.08558 0.08217 -0.0414 1.0000 0.0122
-8.500 -0.3792 0.08250 0.07917 -0.0416 1.0000 0.0120
-8.250 -0.3904 0.07939 0.07615 -0.0411 1.0000 0.0120
-8.000 -0.4003 0.07625 0.07308 -0.0414 0.9981 0.0118
-7.750 -0.3899 0.06950 0.06635 -0.0508 0.9873 0.0116
-7.500 -0.3741 0.05981 0.05656 -0.0661 0.9767 0.0112
-7.250 -0.3584 0.05125 0.04776 -0.0762 0.9685 0.0110
-7.000 -0.3406 0.04352 0.03967 -0.0830 0.9609 0.0108
-6.750 -0.3227 0.03643 0.03209 -0.0869 0.9532 0.0109
-6.500 -0.3001 0.03058 0.02563 -0.0894 0.9470 0.0115
-6.250 -0.2749 0.02654 0.02092 -0.0906 0.9414 0.0130
-6.000 -0.2495 0.02358 0.01742 -0.0911 0.9353 0.0132
-5.750 -0.2204 0.02097 0.01433 -0.0919 0.9314 0.0135
-5.500 -0.1955 0.01893 0.01200 -0.0917 0.9252 0.0141
-5.250 -0.1672 0.01767 0.01056 -0.0921 0.9203 0.0149
-5.000 -0.1375 0.01665 0.00940 -0.0925 0.9163 0.0160
-4.750 -0.1115 0.01599 0.00860 -0.0923 0.9098 0.0179
-4.500 -0.0827 0.01531 0.00778 -0.0924 0.9051 0.0199
-4.250 -0.0563 0.01438 0.00680 -0.0923 0.8995 0.0223
-4.000 -0.0292 0.01381 0.00614 -0.0922 0.8936 0.0265
-3.750 -0.0005 0.01322 0.00550 -0.0923 0.8892 0.0359
-3.500 0.0253 0.01291 0.00513 -0.0920 0.8821 0.0465
-3.250 0.0534 0.01263 0.00486 -0.0921 0.8768 0.0640
-3.000 0.0802 0.01234 0.00456 -0.0920 0.8706 0.0811
-2.750 0.1073 0.01197 0.00423 -0.0919 0.8645 0.1032
-2.500 0.1343 0.01150 0.00393 -0.0920 0.8589 0.1638
-2.250 0.1594 0.01078 0.00370 -0.0920 0.8519 0.3116
-2.000 0.1845 0.01015 0.00366 -0.0916 0.8465 0.5012
-1.750 0.2093 0.00998 0.00372 -0.0908 0.8388 0.5856
-1.500 0.2361 0.00990 0.00367 -0.0903 0.8329 0.6363
-1.250 0.2611 0.00988 0.00371 -0.0894 0.8244 0.6776
-1.000 0.2864 0.00984 0.00373 -0.0884 0.8172 0.7188
-0.750 0.3119 0.00981 0.00371 -0.0876 0.8087 0.7401
-0.500 0.3391 0.00978 0.00362 -0.0873 0.8011 0.7513
-0.250 0.3666 0.00976 0.00354 -0.0871 0.7936 0.7611
0.000 0.3934 0.00973 0.00350 -0.0867 0.7858 0.7704
0.250 0.4208 0.00970 0.00341 -0.0865 0.7781 0.7804
0.500 0.4473 0.00967 0.00336 -0.0860 0.7668 0.7913
0.750 0.4738 0.00964 0.00330 -0.0855 0.7546 0.8025
1.000 0.5001 0.00961 0.00326 -0.0850 0.7435 0.8145
1.250 0.5265 0.00959 0.00324 -0.0845 0.7340 0.8278
1.500 0.5526 0.00958 0.00324 -0.0840 0.7233 0.8431
1.750 0.5786 0.00956 0.00324 -0.0834 0.7117 0.8612
2.000 0.6050 0.00952 0.00325 -0.0829 0.6987 0.8860
2.250 0.6369 0.00947 0.00323 -0.0835 0.6830 0.9293
2.500 0.6692 0.00952 0.00322 -0.0845 0.6659 1.0000
2.750 0.6959 0.00965 0.00329 -0.0843 0.6486 1.0000
3.000 0.7224 0.00979 0.00340 -0.0840 0.6304 1.0000
3.250 0.7485 0.00995 0.00349 -0.0837 0.6099 1.0000
3.500 0.7742 0.01014 0.00361 -0.0833 0.5859 1.0000
3.750 0.7991 0.01037 0.00374 -0.0827 0.5580 1.0000
4.000 0.8233 0.01065 0.00393 -0.0820 0.5270 1.0000
4.250 0.8468 0.01098 0.00413 -0.0812 0.4930 1.0000
4.500 0.8695 0.01138 0.00438 -0.0804 0.4583 1.0000
4.750 0.8919 0.01182 0.00467 -0.0795 0.4243 1.0000
5.000 0.9142 0.01228 0.00503 -0.0786 0.3914 1.0000
5.250 0.9362 0.01277 0.00540 -0.0778 0.3595 1.0000
5.750 0.9794 0.01380 0.00621 -0.0760 0.3007 1.0000
6.000 1.0008 0.01434 0.00666 -0.0751 0.2743 1.0000
6.250 1.0223 0.01487 0.00716 -0.0742 0.2496 1.0000
6.500 1.0433 0.01543 0.00765 -0.0733 0.2246 1.0000
6.750 1.0639 0.01602 0.00816 -0.0723 0.2003 1.0000
7.000 1.0835 0.01669 0.00870 -0.0713 0.1726 1.0000
7.250 1.1025 0.01740 0.00928 -0.0702 0.1445 1.0000
7.500 1.1210 0.01816 0.00989 -0.0690 0.1164 1.0000
7.750 1.1394 0.01891 0.01054 -0.0678 0.0942 1.0000
8.000 1.1582 0.01961 0.01126 -0.0667 0.0783 1.0000
8.250 1.1763 0.02035 0.01199 -0.0654 0.0649 1.0000
8.500 1.1931 0.02118 0.01279 -0.0640 0.0513 1.0000
8.750 1.2081 0.02214 0.01368 -0.0624 0.0378 1.0000
9.000 1.2225 0.02303 0.01459 -0.0606 0.0282 1.0000
9.250 1.2338 0.02411 0.01562 -0.0584 0.0177 1.0000
9.500 1.2445 0.02523 0.01676 -0.0562 0.0106 1.0000
9.750 1.2560 0.02629 0.01790 -0.0542 0.0084 1.0000
10.000 1.2658 0.02750 0.01924 -0.0520 0.0072 1.0000
10.250 1.2756 0.02872 0.02060 -0.0499 0.0066 1.0000
10.500 1.2845 0.03001 0.02205 -0.0479 0.0062 1.0000
10.750 1.2922 0.03142 0.02362 -0.0460 0.0059 1.0000
11.000 1.2984 0.03298 0.02534 -0.0440 0.0056 1.0000
11.250 1.3035 0.03466 0.02719 -0.0422 0.0055 1.0000
11.500 1.3066 0.03657 0.02927 -0.0404 0.0053 1.0000
11.750 1.3086 0.03864 0.03150 -0.0388 0.0052 1.0000
12.000 1.3083 0.04102 0.03406 -0.0373 0.0051 1.0000
12.250 1.3066 0.04362 0.03683 -0.0360 0.0050 1.0000
12.500 1.3033 0.04654 0.03992 -0.0350 0.0049 1.0000
12.750 1.2994 0.04967 0.04322 -0.0344 0.0049 1.0000
13.000 1.2936 0.05318 0.04691 -0.0341 0.0048 1.0000
13.250 1.2862 0.05709 0.05100 -0.0341 0.0048 1.0000
13.500 1.2787 0.06121 0.05531 -0.0346 0.0048 1.0000
13.750 1.2695 0.06581 0.06007 -0.0355 0.0047 1.0000
14.000 1.2616 0.07047 0.06491 -0.0367 0.0047 1.0000
14.250 1.2528 0.07554 0.07021 -0.0384 0.0047 1.0000
14.500 1.2435 0.08098 0.07584 -0.0405 0.0047 1.0000
14.750 1.2331 0.08687 0.08192 -0.0431 0.0047 1.0000
15.000 1.2217 0.09327 0.08850 -0.0461 0.0047 1.0000
15.250 1.2104 0.09991 0.09532 -0.0495 0.0047 1.0000
15.500 1.1987 0.10687 0.10245 -0.0532 0.0047 1.0000
15.750 1.1866 0.11414 0.10989 -0.0572 0.0047 1.0000
16.000 1.1743 0.12174 0.11765 -0.0615 0.0047 1.0000
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