HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 50,000 Max Cl/Cd: 30.15 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3014-il-50000.txt Download as CSV file: xf-hq3014-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/14 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3060 0.10719 0.10052 -0.0286 1.0000 0.3304
-9.000 -0.3074 0.10494 0.09836 -0.0268 1.0000 0.3436
-8.750 -0.3176 0.10341 0.09694 -0.0245 1.0000 0.3553
-8.500 -0.3432 0.10368 0.09737 -0.0211 1.0000 0.3674
-8.250 -0.3321 0.10043 0.09414 -0.0188 1.0000 0.3812
-8.000 -0.3319 0.09833 0.09209 -0.0159 1.0000 0.3956
-7.750 -0.3317 0.09618 0.08999 -0.0131 1.0000 0.4088
-7.000 -0.5968 0.07019 0.06427 -0.0356 1.0000 0.1644
-6.750 -0.6126 0.06278 0.05627 -0.0382 1.0000 0.1505
-6.500 -0.6063 0.05855 0.05184 -0.0378 1.0000 0.1492
-6.250 -0.5984 0.05427 0.04725 -0.0377 1.0000 0.1480
-6.000 -0.5882 0.05010 0.04247 -0.0382 1.0000 0.1491
-5.750 -0.5734 0.04638 0.03818 -0.0384 1.0000 0.1510
-5.500 -0.5567 0.04403 0.03585 -0.0377 1.0000 0.1565
-5.250 -0.5376 0.04143 0.03272 -0.0376 1.0000 0.1620
-5.000 -0.5168 0.03899 0.02973 -0.0375 1.0000 0.1668
-4.750 -0.4972 0.03737 0.02807 -0.0368 1.0000 0.1745
-4.500 -0.4745 0.03564 0.02579 -0.0364 1.0000 0.1799
-4.250 -0.4543 0.03425 0.02441 -0.0357 1.0000 0.1888
-4.000 -0.4329 0.03306 0.02302 -0.0350 1.0000 0.1993
-3.750 -0.4112 0.03206 0.02185 -0.0341 1.0000 0.2106
-3.500 -0.3906 0.03118 0.02097 -0.0332 1.0000 0.2272
-3.250 -0.3708 0.03027 0.02026 -0.0322 1.0000 0.2485
-3.000 -0.3504 0.02931 0.01950 -0.0312 1.0000 0.2828
-2.750 -0.3293 0.02769 0.01889 -0.0306 1.0000 0.3781
-2.500 -0.3302 0.02790 0.02059 -0.0221 1.0000 0.6380
-2.250 -0.3310 0.02875 0.02151 -0.0143 1.0000 0.7166
-2.000 -0.3297 0.02920 0.02192 -0.0077 1.0000 0.7675
-1.750 -0.3274 0.02935 0.02200 -0.0017 1.0000 0.8110
-1.500 -0.3244 0.02929 0.02189 0.0040 1.0000 0.8541
-1.250 -0.3141 0.02923 0.02180 0.0083 1.0000 0.9027
-1.000 -0.1552 0.03266 0.02464 -0.0142 1.0000 1.0000
-0.750 -0.1622 0.03197 0.02388 -0.0115 1.0000 1.0000
-0.500 -0.1680 0.03127 0.02311 -0.0089 1.0000 1.0000
-0.250 -0.1585 0.03112 0.02280 -0.0090 0.9971 1.0000
0.000 -0.1204 0.03211 0.02355 -0.0140 0.9855 1.0000
0.250 -0.0824 0.03315 0.02437 -0.0186 0.9734 1.0000
0.500 -0.0462 0.03418 0.02518 -0.0227 0.9617 1.0000
0.750 -0.0084 0.03532 0.02612 -0.0269 0.9491 1.0000
1.000 0.0299 0.03653 0.02715 -0.0309 0.9365 1.0000
1.250 0.0688 0.03778 0.02822 -0.0349 0.9232 1.0000
1.500 0.1076 0.03903 0.02933 -0.0386 0.9095 1.0000
1.750 0.1452 0.04021 0.03037 -0.0419 0.8947 1.0000
2.000 0.1811 0.04132 0.03138 -0.0447 0.8794 1.0000
2.250 0.2145 0.04234 0.03229 -0.0469 0.8633 1.0000
2.500 0.2471 0.04334 0.03322 -0.0489 0.8469 1.0000
2.750 0.2793 0.04434 0.03415 -0.0507 0.8305 1.0000
3.000 0.3109 0.04533 0.03508 -0.0523 0.8144 1.0000
3.250 0.3418 0.04628 0.03600 -0.0537 0.7981 1.0000
3.500 0.3721 0.04723 0.03692 -0.0549 0.7818 1.0000
3.750 0.4022 0.04815 0.03783 -0.0559 0.7655 1.0000
4.000 0.4325 0.04903 0.03871 -0.0569 0.7489 1.0000
4.250 0.4635 0.04984 0.03954 -0.0578 0.7322 1.0000
4.500 0.4957 0.05057 0.04028 -0.0586 0.7155 1.0000
4.750 0.5297 0.05113 0.04088 -0.0594 0.6988 1.0000
5.000 0.5653 0.05152 0.04133 -0.0601 0.6822 1.0000
5.250 0.6023 0.05171 0.04158 -0.0607 0.6659 1.0000
5.500 0.6276 0.05227 0.04218 -0.0603 0.6482 1.0000
5.750 0.6455 0.05315 0.04313 -0.0594 0.6292 1.0000
6.000 0.6730 0.05353 0.04358 -0.0590 0.6119 1.0000
6.250 0.7035 0.05365 0.04378 -0.0586 0.5952 1.0000
6.500 0.7359 0.05352 0.04376 -0.0581 0.5789 1.0000
6.750 0.7678 0.05330 0.04364 -0.0575 0.5632 1.0000
7.000 0.8018 0.05276 0.04320 -0.0567 0.5478 1.0000
7.250 0.8375 0.05188 0.04246 -0.0557 0.5330 1.0000
7.500 0.8791 0.05022 0.04094 -0.0546 0.5186 1.0000
7.750 0.9408 0.04690 0.03781 -0.0544 0.5043 1.0000
8.000 1.0383 0.04170 0.03281 -0.0576 0.4863 1.0000
8.250 1.1052 0.03931 0.03043 -0.0596 0.4655 1.0000
8.500 1.1214 0.04021 0.03140 -0.0577 0.4464 1.0000
8.750 1.1509 0.04051 0.03175 -0.0571 0.4270 1.0000
9.000 1.2020 0.03987 0.03095 -0.0585 0.4056 1.0000
9.250 1.2159 0.04126 0.03243 -0.0566 0.3887 1.0000
9.500 1.2306 0.04260 0.03384 -0.0549 0.3722 1.0000
9.750 1.2465 0.04398 0.03532 -0.0533 0.3563 1.0000
10.000 1.2619 0.04539 0.03679 -0.0517 0.3407 1.0000
10.250 1.2772 0.04687 0.03833 -0.0501 0.3257 1.0000
10.500 1.2923 0.04842 0.03993 -0.0485 0.3111 1.0000
10.750 1.3073 0.05000 0.04156 -0.0470 0.2966 1.0000
11.000 1.3234 0.05166 0.04328 -0.0456 0.2824 1.0000
11.250 1.3020 0.05481 0.04673 -0.0411 0.2751 1.0000
11.500 1.0553 0.07947 0.07163 -0.0361 0.3024 1.0000
11.750 1.0982 0.07699 0.06931 -0.0335 0.2877 1.0000
12.000 1.0438 0.08877 0.08105 -0.0364 0.2844 1.0000
12.250 0.8385 0.12865 0.12037 -0.0573 0.3087 1.0000
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