HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/9 AIRFOIL (hq159-il) Reynolds number: 200,000 Max Cl/Cd: 68.64 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq159-il-200000.txt Download as CSV file: xf-hq159-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4987 0.10622 0.10261 -0.0150 1.0000 0.0396
-9.750 -0.5026 0.10165 0.09810 -0.0198 1.0000 0.0414
-8.000 -0.5446 0.06609 0.06265 -0.0434 1.0000 0.0436
-7.750 -0.5373 0.06318 0.05979 -0.0426 1.0000 0.0448
-7.500 -0.5344 0.05984 0.05641 -0.0428 1.0000 0.0458
-7.250 -0.5313 0.05642 0.05292 -0.0430 1.0000 0.0475
-7.000 -0.5281 0.05277 0.04914 -0.0430 1.0000 0.0493
-5.750 -0.4946 0.03514 0.02971 -0.0343 1.0000 0.0421
-5.500 -0.4840 0.02773 0.02166 -0.0317 1.0000 0.0299
-5.250 -0.4694 0.02441 0.01797 -0.0299 1.0000 0.0290
-5.000 -0.4515 0.02205 0.01523 -0.0282 1.0000 0.0289
-4.750 -0.4318 0.02024 0.01312 -0.0267 1.0000 0.0293
-4.500 -0.4114 0.01905 0.01165 -0.0253 1.0000 0.0304
-4.250 -0.3781 0.01690 0.00943 -0.0268 0.9970 0.0352
-4.000 -0.3402 0.01598 0.00838 -0.0287 0.9929 0.0419
-3.750 -0.3061 0.01446 0.00690 -0.0303 0.9883 0.0574
-3.500 -0.2684 0.01355 0.00608 -0.0327 0.9838 0.0866
-3.250 -0.2333 0.01272 0.00543 -0.0347 0.9785 0.1352
-3.000 -0.2048 0.01072 0.00502 -0.0364 0.9729 0.4688
-2.750 -0.1687 0.01038 0.00514 -0.0379 0.9687 0.6249
-2.500 -0.1378 0.01033 0.00514 -0.0382 0.9610 0.6784
-2.250 -0.1000 0.01032 0.00514 -0.0399 0.9565 0.7230
-2.000 -0.0676 0.01032 0.00515 -0.0404 0.9497 0.7566
-1.750 -0.0312 0.01030 0.00513 -0.0417 0.9444 0.7860
-1.500 0.0030 0.01026 0.00511 -0.0424 0.9393 0.8167
-1.250 0.0327 0.01017 0.00502 -0.0422 0.9315 0.8390
-1.000 0.0666 0.01004 0.00489 -0.0429 0.9260 0.8592
-0.750 0.0932 0.00993 0.00480 -0.0420 0.9174 0.8803
-0.500 0.1230 0.00981 0.00468 -0.0419 0.9106 0.8999
-0.250 0.1542 0.00971 0.00457 -0.0421 0.9028 0.9156
0.000 0.1883 0.00960 0.00445 -0.0429 0.8940 0.9308
0.250 0.2268 0.00945 0.00425 -0.0445 0.8852 0.9449
0.500 0.2660 0.00932 0.00410 -0.0465 0.8737 0.9590
0.750 0.3071 0.00921 0.00397 -0.0490 0.8618 0.9724
1.000 0.3499 0.00911 0.00384 -0.0519 0.8499 0.9852
1.250 0.3936 0.00903 0.00375 -0.0553 0.8389 0.9993
1.500 0.4107 0.00902 0.00370 -0.0535 0.8259 1.0000
1.750 0.4304 0.00905 0.00368 -0.0520 0.8131 1.0000
2.000 0.4531 0.00908 0.00368 -0.0509 0.7999 1.0000
2.250 0.4771 0.00912 0.00372 -0.0501 0.7861 1.0000
2.500 0.5017 0.00916 0.00374 -0.0492 0.7711 1.0000
2.750 0.5266 0.00921 0.00378 -0.0484 0.7550 1.0000
3.000 0.5517 0.00925 0.00381 -0.0476 0.7372 1.0000
3.250 0.5766 0.00930 0.00383 -0.0467 0.7163 1.0000
3.500 0.6014 0.00935 0.00387 -0.0457 0.6915 1.0000
3.750 0.6258 0.00944 0.00392 -0.0447 0.6606 1.0000
4.000 0.6496 0.00958 0.00397 -0.0436 0.6223 1.0000
4.250 0.6727 0.00980 0.00406 -0.0424 0.5718 1.0000
4.500 0.6945 0.01020 0.00424 -0.0411 0.5063 1.0000
4.750 0.7149 0.01080 0.00450 -0.0397 0.4323 1.0000
5.000 0.7355 0.01147 0.00488 -0.0385 0.3648 1.0000
5.250 0.7568 0.01215 0.00532 -0.0376 0.3110 1.0000
5.500 0.7780 0.01286 0.00581 -0.0367 0.2648 1.0000
5.750 0.7998 0.01354 0.00634 -0.0359 0.2162 1.0000
6.000 0.8197 0.01448 0.00698 -0.0349 0.1477 1.0000
6.250 0.8376 0.01576 0.00790 -0.0336 0.1020 1.0000
6.500 0.8578 0.01679 0.00889 -0.0324 0.0829 1.0000
6.750 0.8774 0.01792 0.01001 -0.0312 0.0722 1.0000
7.000 0.8962 0.01923 0.01126 -0.0300 0.0627 1.0000
7.250 0.9189 0.01976 0.01188 -0.0294 0.0524 1.0000
7.500 0.9401 0.02066 0.01288 -0.0284 0.0433 1.0000
7.750 0.9586 0.02208 0.01443 -0.0271 0.0331 1.0000
8.000 0.9760 0.02377 0.01617 -0.0257 0.0254 1.0000
8.250 0.9954 0.02528 0.01780 -0.0245 0.0219 1.0000
8.500 1.0130 0.02744 0.02005 -0.0232 0.0198 1.0000
8.750 1.0284 0.03154 0.02450 -0.0217 0.0186 1.0000
9.000 1.0442 0.03409 0.02741 -0.0201 0.0182 1.0000
9.250 1.0558 0.03721 0.03093 -0.0182 0.0180 1.0000
9.500 1.0620 0.04081 0.03496 -0.0161 0.0180 1.0000
9.750 1.0623 0.04476 0.03931 -0.0136 0.0181 1.0000
10.000 1.0565 0.04890 0.04382 -0.0111 0.0183 1.0000
10.250 1.0442 0.05311 0.04833 -0.0083 0.0185 1.0000
10.500 1.0285 0.05779 0.05323 -0.0057 0.0189 1.0000
10.750 1.0191 0.06031 0.05594 -0.0038 0.0190 1.0000
11.000 1.0100 0.06293 0.05874 -0.0028 0.0193 1.0000
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Polar data table (+)
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