HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 200,000 Max Cl/Cd: 67.18 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1585-il-200000.txt Download as CSV file: xf-hq1585-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5269 0.08386 0.08047 -0.0253 1.0000 0.0501
-8.500 -0.5378 0.07760 0.07427 -0.0328 1.0000 0.0505
-8.250 -0.5547 0.07205 0.06859 -0.0393 1.0000 0.0509
-8.000 -0.5602 0.06822 0.06456 -0.0418 1.0000 0.0512
-7.750 -0.5679 0.06187 0.05801 -0.0439 1.0000 0.0518
-7.500 -0.5575 0.05644 0.05278 -0.0437 1.0000 0.0534
-7.250 -0.5466 0.05358 0.04992 -0.0434 1.0000 0.0551
-7.000 -0.5378 0.05034 0.04659 -0.0436 1.0000 0.0577
-6.500 -0.5252 0.04222 0.03780 -0.0438 1.0000 0.0671
-6.250 -0.5109 0.04037 0.03602 -0.0426 1.0000 0.0719
-6.000 -0.5038 0.03747 0.03277 -0.0414 1.0000 0.0811
-5.750 -0.4884 0.02830 0.02208 -0.0370 1.0000 0.0397
-5.500 -0.4732 0.02629 0.01982 -0.0349 1.0000 0.0386
-5.250 -0.4580 0.02383 0.01702 -0.0331 1.0000 0.0385
-5.000 -0.4411 0.02121 0.01406 -0.0317 1.0000 0.0405
-4.750 -0.4223 0.01960 0.01234 -0.0304 1.0000 0.0425
-4.500 -0.4019 0.01834 0.01092 -0.0292 1.0000 0.0437
-4.250 -0.3679 0.01712 0.00957 -0.0305 0.9970 0.0467
-4.000 -0.3306 0.01642 0.00869 -0.0324 0.9932 0.0509
-3.750 -0.2975 0.01483 0.00713 -0.0337 0.9891 0.0551
-3.500 -0.2608 0.01406 0.00635 -0.0357 0.9849 0.0626
-3.250 -0.2249 0.01323 0.00551 -0.0377 0.9807 0.0780
-3.000 -0.1943 0.01142 0.00468 -0.0394 0.9755 0.2623
-2.750 -0.1630 0.01021 0.00464 -0.0409 0.9712 0.5449
-2.500 -0.1312 0.01002 0.00479 -0.0414 0.9660 0.6558
-2.250 -0.0993 0.01005 0.00491 -0.0418 0.9601 0.7182
-2.000 -0.0624 0.01010 0.00498 -0.0432 0.9562 0.7621
-1.750 -0.0322 0.01010 0.00501 -0.0432 0.9501 0.7943
-1.500 0.0007 0.01004 0.00496 -0.0438 0.9448 0.8207
-1.250 0.0380 0.00995 0.00483 -0.0453 0.9410 0.8413
-1.000 0.0658 0.00986 0.00475 -0.0449 0.9320 0.8586
-0.750 0.1013 0.00972 0.00461 -0.0458 0.9266 0.8764
-0.500 0.1261 0.00965 0.00455 -0.0446 0.9169 0.8981
-0.250 0.1570 0.00955 0.00446 -0.0445 0.9095 0.9190
0.000 0.1910 0.00942 0.00432 -0.0451 0.9004 0.9385
0.250 0.2308 0.00930 0.00419 -0.0469 0.8901 0.9580
0.500 0.2745 0.00915 0.00401 -0.0497 0.8796 0.9740
0.750 0.3170 0.00901 0.00383 -0.0524 0.8693 0.9871
1.000 0.3555 0.00894 0.00375 -0.0548 0.8585 1.0000
1.250 0.3721 0.00895 0.00374 -0.0529 0.8461 1.0000
1.500 0.3930 0.00899 0.00374 -0.0516 0.8344 1.0000
1.750 0.4168 0.00904 0.00375 -0.0507 0.8228 1.0000
2.000 0.4417 0.00909 0.00378 -0.0499 0.8107 1.0000
2.250 0.4670 0.00914 0.00381 -0.0492 0.7981 1.0000
2.500 0.4923 0.00919 0.00386 -0.0484 0.7832 1.0000
2.750 0.5170 0.00919 0.00385 -0.0474 0.7634 1.0000
3.000 0.5416 0.00914 0.00380 -0.0462 0.7391 1.0000
3.250 0.5662 0.00911 0.00374 -0.0451 0.7095 1.0000
3.500 0.5909 0.00913 0.00368 -0.0440 0.6738 1.0000
3.750 0.6152 0.00925 0.00367 -0.0429 0.6298 1.0000
4.000 0.6389 0.00951 0.00378 -0.0418 0.5751 1.0000
4.250 0.6610 0.00997 0.00392 -0.0406 0.4971 1.0000
4.500 0.6818 0.01066 0.00421 -0.0393 0.4176 1.0000
4.750 0.7037 0.01133 0.00459 -0.0385 0.3515 1.0000
5.000 0.7260 0.01202 0.00502 -0.0377 0.2945 1.0000
5.250 0.7485 0.01270 0.00551 -0.0371 0.2369 1.0000
5.500 0.7676 0.01392 0.00617 -0.0361 0.1323 1.0000
5.750 0.7871 0.01524 0.00716 -0.0349 0.0884 1.0000
6.000 0.8095 0.01613 0.00805 -0.0340 0.0784 1.0000
6.250 0.8306 0.01717 0.00905 -0.0331 0.0712 1.0000
6.500 0.8543 0.01781 0.00978 -0.0325 0.0634 1.0000
6.750 0.8761 0.01877 0.01078 -0.0317 0.0557 1.0000
7.000 0.8957 0.02019 0.01215 -0.0307 0.0475 1.0000
7.250 0.9181 0.02125 0.01335 -0.0298 0.0400 1.0000
7.500 0.9379 0.02363 0.01582 -0.0285 0.0339 1.0000
7.750 0.9597 0.02472 0.01701 -0.0278 0.0291 1.0000
8.000 0.9796 0.02795 0.02037 -0.0269 0.0264 1.0000
8.250 0.9997 0.03039 0.02317 -0.0257 0.0251 1.0000
8.500 1.0184 0.03287 0.02602 -0.0243 0.0244 1.0000
8.750 1.0334 0.03598 0.02957 -0.0227 0.0240 1.0000
9.000 1.0437 0.03965 0.03370 -0.0208 0.0239 1.0000
9.250 1.0491 0.04366 0.03815 -0.0188 0.0240 1.0000
9.500 1.0503 0.04757 0.04247 -0.0166 0.0240 1.0000
9.750 1.0468 0.05142 0.04669 -0.0145 0.0238 1.0000
10.000 1.0386 0.05502 0.05061 -0.0122 0.0234 1.0000
10.250 1.0224 0.05867 0.05450 -0.0096 0.0235 1.0000
10.500 1.0024 0.06257 0.05859 -0.0079 0.0239 1.0000
10.750 0.9822 0.06691 0.06310 -0.0080 0.0241 1.0000
11.000 0.9598 0.07228 0.06863 -0.0098 0.0244 1.0000
11.250 0.9369 0.07879 0.07526 -0.0133 0.0249 1.0000
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Polar data table (+)
Polar graphs
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