HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 100,000 Max Cl/Cd: 49.08 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159b-il-100000-n5.txt Download as CSV file: xf-hq159b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5249 0.08909 0.08411 -0.0235 1.0000 0.0205
-9.250 -0.5269 0.08434 0.07941 -0.0261 1.0000 0.0202
-9.000 -0.5319 0.07873 0.07387 -0.0297 1.0000 0.0201
-8.750 -0.5391 0.07247 0.06767 -0.0346 1.0000 0.0199
-8.500 -0.5512 0.06676 0.06205 -0.0390 1.0000 0.0196
-8.250 -0.5613 0.06150 0.05671 -0.0418 1.0000 0.0194
-8.000 -0.5683 0.05636 0.05141 -0.0435 1.0000 0.0192
-7.750 -0.5719 0.05133 0.04615 -0.0442 1.0000 0.0192
-7.500 -0.5712 0.04666 0.04117 -0.0442 1.0000 0.0192
-7.250 -0.5675 0.04211 0.03622 -0.0435 1.0000 0.0193
-7.000 -0.5604 0.03783 0.03135 -0.0424 1.0000 0.0200
-6.750 -0.5499 0.03388 0.02665 -0.0408 1.0000 0.0213
-6.500 -0.5356 0.03198 0.02467 -0.0399 1.0000 0.0228
-6.250 -0.5196 0.02993 0.02233 -0.0385 1.0000 0.0241
-6.000 -0.5026 0.02754 0.01955 -0.0370 1.0000 0.0254
-5.750 -0.4843 0.02530 0.01690 -0.0354 1.0000 0.0273
-5.500 -0.4658 0.02342 0.01476 -0.0339 1.0000 0.0299
-5.250 -0.4474 0.02275 0.01403 -0.0327 1.0000 0.0349
-5.000 -0.4281 0.02137 0.01243 -0.0312 1.0000 0.0396
-4.750 -0.4095 0.02064 0.01168 -0.0300 1.0000 0.0467
-4.500 -0.3831 0.01947 0.01034 -0.0300 0.9974 0.0529
-4.250 -0.3502 0.01845 0.00929 -0.0314 0.9917 0.0599
-4.000 -0.3169 0.01769 0.00842 -0.0330 0.9856 0.0710
-3.750 -0.2833 0.01692 0.00756 -0.0345 0.9800 0.0812
-3.500 -0.2506 0.01622 0.00686 -0.0359 0.9735 0.0977
-3.000 -0.1883 0.01409 0.00582 -0.0389 0.9615 0.3231
-2.750 -0.1586 0.01324 0.00584 -0.0395 0.9563 0.5439
-2.500 -0.1302 0.01312 0.00592 -0.0392 0.9491 0.6400
-2.250 -0.0990 0.01311 0.00596 -0.0393 0.9431 0.7041
-2.000 -0.0725 0.01310 0.00600 -0.0384 0.9355 0.7503
-1.750 -0.0424 0.01308 0.00594 -0.0383 0.9293 0.7831
-1.500 -0.0146 0.01305 0.00588 -0.0379 0.9216 0.8083
-1.250 0.0163 0.01299 0.00578 -0.0379 0.9148 0.8347
-1.000 0.0448 0.01292 0.00565 -0.0376 0.9052 0.8561
-0.750 0.0776 0.01281 0.00550 -0.0381 0.8969 0.8729
-0.500 0.1103 0.01272 0.00537 -0.0388 0.8883 0.8880
-0.250 0.1435 0.01267 0.00527 -0.0397 0.8807 0.9036
0.000 0.1802 0.01261 0.00519 -0.0414 0.8740 0.9193
0.250 0.2176 0.01258 0.00514 -0.0433 0.8665 0.9364
0.500 0.2582 0.01251 0.00506 -0.0458 0.8593 0.9534
0.750 0.2985 0.01243 0.00497 -0.0483 0.8479 0.9727
1.000 0.3383 0.01231 0.00482 -0.0506 0.8337 0.9971
1.250 0.3627 0.01227 0.00473 -0.0498 0.8173 1.0000
1.500 0.3853 0.01227 0.00469 -0.0486 0.7998 1.0000
1.750 0.4093 0.01231 0.00470 -0.0478 0.7837 1.0000
2.000 0.4344 0.01237 0.00475 -0.0472 0.7700 1.0000
2.250 0.4599 0.01244 0.00485 -0.0466 0.7557 1.0000
2.500 0.4855 0.01251 0.00494 -0.0460 0.7407 1.0000
2.750 0.5112 0.01260 0.00505 -0.0454 0.7249 1.0000
3.000 0.5369 0.01268 0.00519 -0.0447 0.7075 1.0000
3.250 0.5624 0.01279 0.00533 -0.0441 0.6878 1.0000
3.500 0.5878 0.01290 0.00549 -0.0433 0.6661 1.0000
3.750 0.6127 0.01303 0.00565 -0.0425 0.6388 1.0000
4.000 0.6365 0.01318 0.00574 -0.0413 0.5963 1.0000
4.250 0.6591 0.01343 0.00587 -0.0399 0.5356 1.0000
4.500 0.6802 0.01393 0.00602 -0.0383 0.4654 1.0000
4.750 0.7002 0.01463 0.00636 -0.0370 0.3899 1.0000
5.000 0.7192 0.01551 0.00680 -0.0357 0.3113 1.0000
5.250 0.7396 0.01633 0.00734 -0.0347 0.2567 1.0000
5.500 0.7613 0.01707 0.00793 -0.0340 0.2127 1.0000
5.750 0.7834 0.01779 0.00862 -0.0332 0.1634 1.0000
6.000 0.8027 0.01893 0.00940 -0.0323 0.1047 1.0000
6.250 0.8220 0.02016 0.01048 -0.0312 0.0760 1.0000
6.500 0.8421 0.02128 0.01162 -0.0301 0.0637 1.0000
6.750 0.8622 0.02234 0.01273 -0.0291 0.0553 1.0000
7.000 0.8821 0.02340 0.01386 -0.0281 0.0489 1.0000
7.250 0.9005 0.02473 0.01529 -0.0268 0.0455 1.0000
7.500 0.9200 0.02604 0.01678 -0.0256 0.0421 1.0000
7.750 0.9386 0.02732 0.01811 -0.0246 0.0372 1.0000
8.000 0.9570 0.02906 0.01999 -0.0234 0.0335 1.0000
8.250 0.9764 0.03071 0.02192 -0.0224 0.0303 1.0000
8.500 0.9927 0.03261 0.02381 -0.0215 0.0270 1.0000
8.750 1.0113 0.03475 0.02632 -0.0203 0.0247 1.0000
9.000 1.0281 0.03733 0.02924 -0.0190 0.0230 1.0000
9.250 1.0419 0.03998 0.03221 -0.0176 0.0217 1.0000
9.500 1.0527 0.04228 0.03474 -0.0163 0.0204 1.0000
9.750 1.0594 0.04549 0.03809 -0.0150 0.0192 1.0000
10.000 1.0600 0.04826 0.04137 -0.0127 0.0183 1.0000
10.250 1.0553 0.05152 0.04508 -0.0103 0.0178 1.0000
10.500 1.0436 0.05490 0.04880 -0.0076 0.0175 1.0000
10.750 1.0300 0.05847 0.05265 -0.0058 0.0174 1.0000
11.000 1.0126 0.06260 0.05706 -0.0051 0.0173 1.0000
11.250 0.9942 0.06728 0.06197 -0.0058 0.0173 1.0000
11.500 0.9756 0.07257 0.06747 -0.0078 0.0174 1.0000
11.750 0.9548 0.07898 0.07406 -0.0114 0.0175 1.0000
12.000 0.9356 0.08617 0.08138 -0.0162 0.0177 1.0000
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Polar data table (+)
Polar graphs
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