HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il) Reynolds number: 50,000 Max Cl/Cd: 37.27 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2195-il-50000.txt Download as CSV file: xf-hq2195-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.1/9.5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4187 0.09996 0.09292 -0.0123 1.0000 0.3133
-8.250 -0.4201 0.09764 0.09068 -0.0117 1.0000 0.3302
-8.000 -0.4270 0.09587 0.08901 -0.0110 1.0000 0.3466
-7.750 -0.4019 0.09119 0.08429 -0.0095 1.0000 0.3656
-7.500 -0.4015 0.08924 0.08242 -0.0078 1.0000 0.3898
-7.250 -0.3832 0.08569 0.07888 -0.0060 1.0000 0.4162
-7.000 -0.3750 0.08291 0.07615 -0.0042 1.0000 0.4405
-6.750 -0.3876 0.08216 0.07554 -0.0012 1.0000 0.4654
-6.500 -0.3638 0.07775 0.07112 -0.0006 1.0000 0.4838
-5.750 -0.4898 0.05953 0.05324 -0.0295 1.0000 0.2564
-5.500 -0.4699 0.04714 0.03934 -0.0425 1.0000 0.1547
-5.250 -0.4531 0.04374 0.03570 -0.0421 1.0000 0.1494
-5.000 -0.4344 0.04020 0.03168 -0.0421 1.0000 0.1439
-4.750 -0.4113 0.03726 0.02792 -0.0422 1.0000 0.1374
-4.500 -0.3895 0.03454 0.02484 -0.0416 1.0000 0.1354
-4.250 -0.3663 0.03223 0.02213 -0.0410 1.0000 0.1347
-4.000 -0.3422 0.03047 0.01985 -0.0403 1.0000 0.1379
-3.750 -0.3195 0.02855 0.01787 -0.0395 1.0000 0.1437
-3.500 -0.2955 0.02706 0.01616 -0.0385 1.0000 0.1489
-3.250 -0.2719 0.02564 0.01461 -0.0373 1.0000 0.1575
-3.000 -0.2491 0.02443 0.01343 -0.0361 1.0000 0.1732
-2.750 -0.2265 0.02324 0.01228 -0.0347 1.0000 0.1950
-2.500 -0.2023 0.02162 0.01108 -0.0342 1.0000 0.2496
-2.250 -0.2047 0.01926 0.01153 -0.0253 1.0000 0.7353
-2.000 -0.2167 0.01923 0.01172 -0.0136 1.0000 0.8584
-1.750 -0.1379 0.01929 0.01121 -0.0197 1.0000 1.0000
-1.500 -0.1348 0.01894 0.01066 -0.0177 1.0000 1.0000
-1.250 -0.1188 0.01883 0.01026 -0.0175 1.0000 1.0000
-1.000 -0.0974 0.01887 0.01000 -0.0181 1.0000 1.0000
-0.750 -0.0742 0.01901 0.00986 -0.0187 1.0000 1.0000
-0.500 -0.0504 0.01922 0.00983 -0.0193 1.0000 1.0000
-0.250 -0.0267 0.01948 0.00987 -0.0199 1.0000 1.0000
0.000 -0.0033 0.01979 0.00997 -0.0203 1.0000 1.0000
0.250 0.0197 0.02014 0.01016 -0.0206 1.0000 1.0000
0.500 0.0423 0.02053 0.01041 -0.0209 1.0000 1.0000
0.750 0.0645 0.02097 0.01072 -0.0211 1.0000 1.0000
1.000 0.0863 0.02145 0.01110 -0.0213 1.0000 1.0000
1.250 0.1075 0.02198 0.01156 -0.0215 1.0000 1.0000
1.500 0.1282 0.02258 0.01209 -0.0217 1.0000 1.0000
1.750 0.1482 0.02323 0.01271 -0.0219 1.0000 1.0000
2.000 0.1675 0.02397 0.01342 -0.0221 1.0000 1.0000
2.250 0.2067 0.02520 0.01468 -0.0263 0.9893 1.0000
2.500 0.2678 0.02678 0.01631 -0.0341 0.9659 1.0000
2.750 0.3288 0.02812 0.01775 -0.0413 0.9416 1.0000
3.000 0.3807 0.02908 0.01885 -0.0466 0.9149 1.0000
3.250 0.4322 0.02987 0.01979 -0.0513 0.8876 1.0000
3.500 0.4845 0.03042 0.02054 -0.0555 0.8597 1.0000
3.750 0.5383 0.03067 0.02103 -0.0593 0.8320 1.0000
4.000 0.5999 0.03038 0.02103 -0.0635 0.8055 1.0000
4.250 0.6513 0.02984 0.02078 -0.0653 0.7777 1.0000
4.500 0.6965 0.02907 0.02026 -0.0656 0.7488 1.0000
4.750 0.7412 0.02783 0.01926 -0.0649 0.7186 1.0000
5.000 0.7773 0.02663 0.01826 -0.0628 0.6837 1.0000
5.250 0.8130 0.02515 0.01689 -0.0601 0.6451 1.0000
5.500 0.8424 0.02407 0.01582 -0.0571 0.6007 1.0000
5.750 0.8670 0.02361 0.01528 -0.0540 0.5487 1.0000
6.000 0.8896 0.02387 0.01523 -0.0510 0.4884 1.0000
6.250 0.9073 0.02496 0.01588 -0.0480 0.4174 1.0000
6.500 0.9218 0.02662 0.01705 -0.0450 0.3410 1.0000
6.750 0.9370 0.02836 0.01839 -0.0424 0.2792 1.0000
7.000 0.9551 0.03006 0.01981 -0.0406 0.2348 1.0000
7.250 0.9759 0.03192 0.02137 -0.0393 0.2013 1.0000
7.500 0.9980 0.03402 0.02338 -0.0382 0.1755 1.0000
7.750 1.0211 0.03656 0.02601 -0.0373 0.1571 1.0000
8.000 1.0449 0.03941 0.02899 -0.0366 0.1445 1.0000
8.250 1.0654 0.04208 0.03188 -0.0356 0.1339 1.0000
8.500 1.0815 0.04573 0.03604 -0.0341 0.1290 1.0000
8.750 1.0929 0.04952 0.04040 -0.0323 0.1257 1.0000
9.000 1.1068 0.05293 0.04405 -0.0311 0.1211 1.0000
9.250 1.1174 0.05705 0.04839 -0.0299 0.1175 1.0000
9.500 1.1154 0.06146 0.05334 -0.0278 0.1169 1.0000
9.750 1.1114 0.06628 0.05859 -0.0260 0.1172 1.0000
10.000 1.1059 0.07134 0.06396 -0.0246 0.1178 1.0000
10.250 1.0720 0.07628 0.06937 -0.0224 0.1204 1.0000
10.500 1.0094 0.08279 0.07615 -0.0218 0.1250 1.0000
10.750 0.9758 0.09022 0.08364 -0.0246 0.1286 1.0000
11.000 0.9592 0.09734 0.09078 -0.0275 0.1308 1.0000
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Polar data table (+)
Polar graphs
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