HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 AIRFOIL (hq259-il) Reynolds number: 200,000 Max Cl/Cd: 79.98 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259-il-200000.txt Download as CSV file: xf-hq259-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4073 0.08675 0.08344 -0.0406 1.0000 0.0364
-8.000 -0.4150 0.08338 0.08015 -0.0423 1.0000 0.0365
-7.750 -0.4217 0.07935 0.07615 -0.0459 1.0000 0.0365
-7.500 -0.4279 0.07615 0.07294 -0.0467 1.0000 0.0366
-7.250 -0.4371 0.07326 0.07002 -0.0463 1.0000 0.0366
-7.000 -0.4457 0.07063 0.06733 -0.0450 1.0000 0.0367
-6.750 -0.4609 0.06477 0.06150 -0.0442 1.0000 0.0373
-6.500 -0.4634 0.06145 0.05826 -0.0421 1.0000 0.0381
-6.250 -0.4638 0.05890 0.05571 -0.0405 1.0000 0.0388
-6.000 -0.4622 0.05635 0.05314 -0.0393 1.0000 0.0398
-5.750 -0.4380 0.05210 0.04874 -0.0434 0.9966 0.0423
-5.500 -0.3934 0.04880 0.04461 -0.0505 0.9908 0.0492
-5.250 -0.3733 0.04147 0.03737 -0.0543 0.9869 0.0524
-5.000 -0.3357 0.03809 0.03339 -0.0588 0.9829 0.0639
-4.750 -0.3078 0.03452 0.02985 -0.0607 0.9785 0.0671
-4.500 -0.2673 0.02706 0.02129 -0.0612 0.9747 0.0344
-4.250 -0.2315 0.02272 0.01633 -0.0627 0.9718 0.0299
-4.000 -0.1934 0.01984 0.01287 -0.0641 0.9695 0.0286
-3.750 -0.1612 0.01821 0.01102 -0.0647 0.9648 0.0299
-3.500 -0.1265 0.01719 0.00983 -0.0658 0.9603 0.0350
-3.250 -0.0896 0.01571 0.00833 -0.0676 0.9572 0.0429
-3.000 -0.0536 0.01449 0.00713 -0.0693 0.9536 0.0668
-2.750 -0.0223 0.01390 0.00660 -0.0703 0.9473 0.1010
-2.500 0.0130 0.01216 0.00585 -0.0729 0.9439 0.3200
-2.250 0.0437 0.01126 0.00602 -0.0734 0.9401 0.6424
-2.000 0.0722 0.01121 0.00605 -0.0731 0.9331 0.7064
-1.750 0.1090 0.01112 0.00595 -0.0743 0.9295 0.7486
-1.500 0.1368 0.01107 0.00589 -0.0738 0.9224 0.7801
-1.250 0.1676 0.01093 0.00578 -0.0737 0.9171 0.8154
-1.000 0.1903 0.01079 0.00571 -0.0715 0.9101 0.8578
-0.750 0.2156 0.01056 0.00553 -0.0701 0.9036 0.8889
-0.500 0.2449 0.01040 0.00534 -0.0699 0.8973 0.9094
-0.250 0.2792 0.01025 0.00516 -0.0709 0.8908 0.9304
0.000 0.3232 0.01005 0.00492 -0.0739 0.8871 0.9519
0.250 0.3675 0.00991 0.00474 -0.0774 0.8783 0.9773
0.500 0.4073 0.00970 0.00447 -0.0798 0.8685 1.0000
0.750 0.4326 0.00960 0.00427 -0.0792 0.8574 1.0000
1.000 0.4594 0.00956 0.00416 -0.0790 0.8472 1.0000
1.250 0.4854 0.00958 0.00414 -0.0786 0.8360 1.0000
1.500 0.5121 0.00959 0.00410 -0.0782 0.8251 1.0000
1.750 0.5390 0.00958 0.00405 -0.0778 0.8140 1.0000
2.000 0.5658 0.00957 0.00400 -0.0774 0.8020 1.0000
2.250 0.5924 0.00957 0.00397 -0.0769 0.7893 1.0000
2.500 0.6189 0.00958 0.00399 -0.0763 0.7757 1.0000
2.750 0.6451 0.00961 0.00400 -0.0757 0.7609 1.0000
3.000 0.6711 0.00963 0.00401 -0.0751 0.7444 1.0000
3.250 0.6972 0.00966 0.00402 -0.0744 0.7264 1.0000
3.500 0.7230 0.00972 0.00406 -0.0738 0.7063 1.0000
3.750 0.7486 0.00980 0.00415 -0.0730 0.6842 1.0000
4.000 0.7737 0.00991 0.00424 -0.0723 0.6583 1.0000
4.250 0.7984 0.01006 0.00434 -0.0714 0.6283 1.0000
4.500 0.8222 0.01028 0.00449 -0.0704 0.5902 1.0000
4.750 0.8449 0.01060 0.00470 -0.0692 0.5429 1.0000
5.000 0.8660 0.01107 0.00495 -0.0679 0.4864 1.0000
5.250 0.8861 0.01169 0.00532 -0.0665 0.4285 1.0000
5.500 0.9062 0.01237 0.00577 -0.0652 0.3759 1.0000
5.750 0.9265 0.01307 0.00628 -0.0640 0.3301 1.0000
6.000 0.9462 0.01382 0.00683 -0.0629 0.2871 1.0000
6.250 0.9658 0.01457 0.00735 -0.0618 0.2379 1.0000
6.500 0.9866 0.01525 0.00794 -0.0609 0.1992 1.0000
6.750 1.0064 0.01603 0.00849 -0.0599 0.1536 1.0000
7.000 1.0252 0.01701 0.00918 -0.0588 0.1005 1.0000
7.250 1.0342 0.01936 0.01092 -0.0561 0.0261 1.0000
7.500 1.0519 0.02058 0.01228 -0.0544 0.0214 1.0000
7.750 1.0642 0.02231 0.01418 -0.0520 0.0187 1.0000
8.000 1.0802 0.02358 0.01557 -0.0502 0.0171 1.0000
8.250 1.0965 0.02482 0.01694 -0.0486 0.0152 1.0000
8.500 1.1106 0.02648 0.01873 -0.0466 0.0145 1.0000
8.750 1.1255 0.02832 0.02070 -0.0448 0.0140 1.0000
9.000 1.1415 0.03041 0.02302 -0.0431 0.0136 1.0000
9.250 1.1585 0.03285 0.02569 -0.0417 0.0136 1.0000
9.500 1.1742 0.03570 0.02884 -0.0401 0.0137 1.0000
9.750 1.1859 0.03900 0.03254 -0.0381 0.0141 1.0000
10.000 1.1913 0.04271 0.03668 -0.0355 0.0147 1.0000
10.250 1.1888 0.04643 0.04081 -0.0324 0.0152 1.0000
10.500 1.1797 0.04992 0.04464 -0.0288 0.0157 1.0000
10.750 1.1671 0.05345 0.04846 -0.0257 0.0161 1.0000
11.000 1.1513 0.05727 0.05256 -0.0232 0.0164 1.0000
11.250 1.1345 0.06133 0.05685 -0.0218 0.0167 1.0000
11.500 1.1157 0.06588 0.06163 -0.0214 0.0169 1.0000
11.750 1.0975 0.07076 0.06671 -0.0220 0.0171 1.0000
12.000 1.0767 0.07650 0.07264 -0.0239 0.0172 1.0000
12.250 1.0572 0.08266 0.07897 -0.0269 0.0174 1.0000
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Polar data table (+)
Polar graphs
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