HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 AIRFOIL (hq159-il) Reynolds number: 100,000 Max Cl/Cd: 49.33 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159-il-100000-n5.txt Download as CSV file: xf-hq159-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5110 0.08916 0.08425 -0.0237 1.0000 0.0219
-9.000 -0.5136 0.08421 0.07937 -0.0264 1.0000 0.0216
-8.750 -0.5173 0.07907 0.07429 -0.0296 1.0000 0.0213
-8.500 -0.5230 0.07345 0.06874 -0.0339 1.0000 0.0210
-8.250 -0.5344 0.06784 0.06315 -0.0384 1.0000 0.0207
-8.000 -0.5426 0.06258 0.05782 -0.0411 1.0000 0.0205
-7.750 -0.5468 0.05788 0.05299 -0.0427 1.0000 0.0201
-7.500 -0.5493 0.05301 0.04792 -0.0435 1.0000 0.0199
-7.250 -0.5486 0.04832 0.04296 -0.0435 1.0000 0.0198
-7.000 -0.5446 0.04394 0.03825 -0.0429 1.0000 0.0197
-6.750 -0.5377 0.03989 0.03381 -0.0419 1.0000 0.0196
-6.500 -0.5280 0.03609 0.02955 -0.0405 1.0000 0.0198
-6.250 -0.5154 0.03274 0.02572 -0.0390 1.0000 0.0202
-6.000 -0.5005 0.02981 0.02233 -0.0373 1.0000 0.0207
-5.750 -0.4835 0.02744 0.01950 -0.0357 1.0000 0.0218
-5.500 -0.4656 0.02554 0.01723 -0.0341 1.0000 0.0242
-5.250 -0.4482 0.02394 0.01551 -0.0328 1.0000 0.0264
-5.000 -0.4292 0.02243 0.01381 -0.0313 1.0000 0.0281
-4.750 -0.4099 0.02106 0.01222 -0.0298 1.0000 0.0304
-4.500 -0.3906 0.01987 0.01084 -0.0282 1.0000 0.0336
-4.250 -0.3576 0.01876 0.00970 -0.0298 0.9947 0.0424
-4.000 -0.3247 0.01771 0.00858 -0.0312 0.9886 0.0559
-3.750 -0.2911 0.01686 0.00774 -0.0328 0.9830 0.0782
-3.500 -0.2585 0.01605 0.00699 -0.0342 0.9764 0.1080
-3.250 -0.2252 0.01506 0.00636 -0.0361 0.9710 0.1891
-3.000 -0.1971 0.01384 0.00595 -0.0371 0.9638 0.3756
-2.750 -0.1661 0.01321 0.00602 -0.0377 0.9586 0.5667
-2.500 -0.1377 0.01310 0.00603 -0.0374 0.9506 0.6470
-2.250 -0.1048 0.01308 0.00600 -0.0379 0.9452 0.7052
-2.000 -0.0782 0.01307 0.00601 -0.0370 0.9368 0.7512
-1.750 -0.0463 0.01303 0.00595 -0.0372 0.9312 0.7851
-1.500 -0.0194 0.01299 0.00587 -0.0366 0.9225 0.8125
-1.250 0.0126 0.01292 0.00573 -0.0368 0.9166 0.8390
-1.000 0.0415 0.01285 0.00561 -0.0368 0.9081 0.8589
-0.750 0.0752 0.01277 0.00547 -0.0377 0.9014 0.8749
-0.500 0.1084 0.01269 0.00536 -0.0386 0.8933 0.8910
-0.250 0.1444 0.01263 0.00524 -0.0400 0.8856 0.9074
0.000 0.1839 0.01256 0.00514 -0.0422 0.8781 0.9244
0.250 0.2232 0.01251 0.00508 -0.0445 0.8695 0.9435
0.500 0.2661 0.01243 0.00497 -0.0475 0.8624 0.9615
0.750 0.3060 0.01237 0.00490 -0.0501 0.8511 0.9839
1.000 0.3398 0.01230 0.00480 -0.0513 0.8373 1.0000
1.250 0.3635 0.01227 0.00472 -0.0503 0.8212 1.0000
1.500 0.3863 0.01229 0.00468 -0.0491 0.8034 1.0000
1.750 0.4105 0.01232 0.00468 -0.0483 0.7873 1.0000
2.000 0.4356 0.01238 0.00473 -0.0476 0.7728 1.0000
2.250 0.4609 0.01244 0.00479 -0.0470 0.7580 1.0000
2.500 0.4864 0.01251 0.00490 -0.0463 0.7423 1.0000
2.750 0.5120 0.01258 0.00498 -0.0456 0.7256 1.0000
3.000 0.5372 0.01268 0.00510 -0.0449 0.7064 1.0000
3.250 0.5625 0.01277 0.00521 -0.0441 0.6855 1.0000
3.500 0.5875 0.01288 0.00539 -0.0433 0.6614 1.0000
3.750 0.6123 0.01301 0.00552 -0.0424 0.6328 1.0000
4.000 0.6364 0.01318 0.00566 -0.0414 0.5960 1.0000
4.250 0.6597 0.01343 0.00579 -0.0401 0.5477 1.0000
4.500 0.6817 0.01382 0.00596 -0.0388 0.4869 1.0000
4.750 0.7024 0.01441 0.00630 -0.0374 0.4195 1.0000
5.000 0.7227 0.01512 0.00672 -0.0362 0.3547 1.0000
5.250 0.7432 0.01588 0.00722 -0.0351 0.2997 1.0000
5.500 0.7640 0.01665 0.00780 -0.0342 0.2562 1.0000
5.750 0.7859 0.01735 0.00843 -0.0334 0.2170 1.0000
6.000 0.8074 0.01810 0.00909 -0.0326 0.1754 1.0000
6.250 0.8276 0.01905 0.00989 -0.0317 0.1298 1.0000
6.500 0.8474 0.02010 0.01081 -0.0307 0.1012 1.0000
6.750 0.8671 0.02118 0.01186 -0.0296 0.0840 1.0000
7.000 0.8869 0.02224 0.01293 -0.0286 0.0709 1.0000
7.250 0.9061 0.02339 0.01418 -0.0274 0.0622 1.0000
7.500 0.9237 0.02474 0.01555 -0.0262 0.0546 1.0000
7.750 0.9436 0.02572 0.01666 -0.0253 0.0443 1.0000
8.000 0.9634 0.02670 0.01777 -0.0245 0.0338 1.0000
8.250 0.9795 0.02833 0.01965 -0.0230 0.0269 1.0000
8.500 0.9937 0.03015 0.02157 -0.0215 0.0222 1.0000
8.750 1.0079 0.03240 0.02405 -0.0198 0.0197 1.0000
9.000 1.0236 0.03426 0.02617 -0.0184 0.0169 1.0000
9.250 1.0369 0.03582 0.02789 -0.0171 0.0149 1.0000
9.500 1.0461 0.03812 0.03037 -0.0156 0.0137 1.0000
9.750 1.0529 0.04121 0.03375 -0.0137 0.0132 1.0000
10.000 1.0580 0.04417 0.03710 -0.0118 0.0128 1.0000
10.250 1.0568 0.04723 0.04052 -0.0094 0.0126 1.0000
10.500 1.0502 0.05049 0.04411 -0.0070 0.0124 1.0000
10.750 1.0400 0.05395 0.04788 -0.0052 0.0123 1.0000
11.000 1.0264 0.05788 0.05210 -0.0043 0.0122 1.0000
11.250 1.0110 0.06226 0.05674 -0.0045 0.0122 1.0000
11.500 0.9940 0.06727 0.06198 -0.0059 0.0123 1.0000
11.750 0.9756 0.07313 0.06804 -0.0088 0.0123 1.0000
12.000 0.9567 0.07989 0.07498 -0.0129 0.0124 1.0000
12.250 0.9371 0.08789 0.08312 -0.0185 0.0126 1.0000
12.500 0.9170 0.09726 0.09261 -0.0251 0.0128 1.0000
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