HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 100,000 Max Cl/Cd: 45.1 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1012-il-100000-n5.txt Download as CSV file: xf-hq1012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6612 0.09127 0.08612 -0.0279 1.0000 0.0252
-12.250 -0.6848 0.08154 0.07635 -0.0343 1.0000 0.0247
-12.000 -0.7108 0.07263 0.06734 -0.0408 1.0000 0.0242
-11.750 -0.7351 0.06549 0.06005 -0.0457 1.0000 0.0239
-11.500 -0.7577 0.05967 0.05408 -0.0490 1.0000 0.0238
-11.250 -0.7789 0.05479 0.04897 -0.0507 1.0000 0.0239
-11.000 -0.7967 0.05082 0.04475 -0.0508 1.0000 0.0241
-10.750 -0.8117 0.04754 0.04120 -0.0494 1.0000 0.0243
-10.500 -0.8226 0.04464 0.03797 -0.0471 1.0000 0.0249
-10.250 -0.8248 0.04200 0.03504 -0.0453 1.0000 0.0258
-10.000 -0.8180 0.04029 0.03326 -0.0440 1.0000 0.0268
-9.750 -0.8096 0.03868 0.03152 -0.0426 1.0000 0.0282
-9.500 -0.8007 0.03666 0.02925 -0.0410 1.0000 0.0297
-9.250 -0.7899 0.03438 0.02664 -0.0394 1.0000 0.0313
-9.000 -0.7765 0.03227 0.02417 -0.0378 1.0000 0.0331
-8.750 -0.7628 0.03071 0.02257 -0.0364 1.0000 0.0354
-8.500 -0.7479 0.02969 0.02149 -0.0350 1.0000 0.0385
-8.250 -0.7319 0.02835 0.01992 -0.0334 1.0000 0.0419
-8.000 -0.7170 0.02698 0.01844 -0.0318 1.0000 0.0453
-7.750 -0.7022 0.02612 0.01756 -0.0301 1.0000 0.0495
-7.500 -0.6864 0.02519 0.01643 -0.0283 1.0000 0.0543
-7.250 -0.6734 0.02421 0.01550 -0.0264 1.0000 0.0589
-7.000 -0.6599 0.02348 0.01470 -0.0243 1.0000 0.0641
-6.750 -0.6473 0.02272 0.01386 -0.0220 1.0000 0.0692
-6.500 -0.6312 0.02200 0.01315 -0.0206 0.9985 0.0753
-6.250 -0.5984 0.02108 0.01214 -0.0223 0.9906 0.0841
-6.000 -0.5645 0.02031 0.01127 -0.0241 0.9835 0.0946
-5.750 -0.5335 0.01946 0.01044 -0.0255 0.9753 0.1060
-5.500 -0.5004 0.01868 0.00971 -0.0272 0.9684 0.1242
-5.250 -0.4693 0.01793 0.00906 -0.0285 0.9605 0.1514
-5.000 -0.4368 0.01719 0.00850 -0.0302 0.9538 0.1954
-4.750 -0.4072 0.01649 0.00800 -0.0312 0.9456 0.2500
-4.500 -0.3787 0.01574 0.00756 -0.0319 0.9378 0.3156
-4.250 -0.3508 0.01510 0.00729 -0.0324 0.9300 0.4041
-4.000 -0.3238 0.01474 0.00722 -0.0322 0.9219 0.4832
-3.750 -0.2938 0.01461 0.00722 -0.0324 0.9150 0.5438
-3.500 -0.2661 0.01460 0.00722 -0.0320 0.9069 0.5868
-3.250 -0.2358 0.01462 0.00722 -0.0321 0.9003 0.6207
-3.000 -0.2088 0.01468 0.00723 -0.0316 0.8921 0.6485
-2.750 -0.1791 0.01473 0.00724 -0.0315 0.8855 0.6697
-2.500 -0.1525 0.01476 0.00720 -0.0310 0.8772 0.6859
-2.250 -0.1230 0.01476 0.00713 -0.0309 0.8706 0.7001
-2.000 -0.0968 0.01478 0.00709 -0.0304 0.8622 0.7130
-1.750 -0.0682 0.01478 0.00702 -0.0302 0.8558 0.7263
-1.500 -0.0432 0.01483 0.00705 -0.0293 0.8473 0.7411
-1.250 -0.0158 0.01486 0.00704 -0.0287 0.8408 0.7563
-1.000 0.0087 0.01489 0.00706 -0.0278 0.8320 0.7696
-0.750 0.0366 0.01486 0.00697 -0.0275 0.8257 0.7808
-0.500 0.0618 0.01487 0.00698 -0.0268 0.8166 0.7890
-0.250 0.0896 0.01482 0.00688 -0.0266 0.8100 0.7982
0.000 0.1150 0.01483 0.00689 -0.0260 0.8011 0.8072
0.250 0.1425 0.01480 0.00685 -0.0257 0.7942 0.8160
0.500 0.1683 0.01479 0.00684 -0.0252 0.7855 0.8261
0.750 0.1952 0.01476 0.00682 -0.0247 0.7765 0.8348
1.000 0.2224 0.01467 0.00671 -0.0241 0.7668 0.8442
1.250 0.2475 0.01460 0.00665 -0.0233 0.7541 0.8548
1.500 0.2740 0.01452 0.00658 -0.0226 0.7410 0.8641
1.750 0.3007 0.01444 0.00652 -0.0220 0.7279 0.8743
2.000 0.3279 0.01438 0.00650 -0.0216 0.7159 0.8854
2.250 0.3570 0.01434 0.00649 -0.0216 0.7052 0.8964
2.500 0.3879 0.01431 0.00650 -0.0219 0.6936 0.9070
2.750 0.4195 0.01430 0.00657 -0.0225 0.6804 0.9183
3.000 0.4526 0.01429 0.00662 -0.0234 0.6662 0.9303
3.250 0.4868 0.01428 0.00666 -0.0246 0.6507 0.9432
3.500 0.5220 0.01428 0.00672 -0.0260 0.6331 0.9564
4.000 0.5949 0.01431 0.00684 -0.0295 0.5857 0.9845
4.250 0.6284 0.01438 0.00690 -0.0308 0.5539 1.0000
4.500 0.6449 0.01452 0.00695 -0.0288 0.5221 1.0000
4.750 0.6629 0.01475 0.00704 -0.0270 0.4849 1.0000
5.000 0.6814 0.01511 0.00719 -0.0253 0.4431 1.0000
5.250 0.6998 0.01557 0.00744 -0.0237 0.4001 1.0000
5.500 0.7186 0.01611 0.00781 -0.0223 0.3593 1.0000
5.750 0.7376 0.01670 0.00822 -0.0210 0.3238 1.0000
6.000 0.7569 0.01731 0.00868 -0.0198 0.2948 1.0000
6.250 0.7766 0.01792 0.00919 -0.0187 0.2712 1.0000
6.500 0.7969 0.01852 0.00977 -0.0177 0.2500 1.0000
6.750 0.8170 0.01913 0.01036 -0.0167 0.2290 1.0000
7.000 0.8370 0.01975 0.01096 -0.0157 0.2074 1.0000
7.250 0.8566 0.02039 0.01157 -0.0146 0.1853 1.0000
7.500 0.8757 0.02107 0.01223 -0.0135 0.1638 1.0000
7.750 0.8939 0.02184 0.01297 -0.0124 0.1445 1.0000
8.000 0.9113 0.02268 0.01377 -0.0111 0.1291 1.0000
8.250 0.9282 0.02357 0.01464 -0.0098 0.1158 1.0000
8.500 0.9448 0.02449 0.01559 -0.0085 0.1044 1.0000
8.750 0.9604 0.02550 0.01661 -0.0070 0.0956 1.0000
9.000 0.9746 0.02656 0.01766 -0.0056 0.0875 1.0000
9.250 0.9902 0.02754 0.01875 -0.0042 0.0792 1.0000
9.500 1.0020 0.02872 0.01994 -0.0025 0.0732 1.0000
9.750 1.0154 0.02976 0.02115 -0.0008 0.0669 1.0000
10.000 1.0239 0.03103 0.02242 0.0012 0.0622 1.0000
10.250 1.0352 0.03228 0.02385 0.0029 0.0570 1.0000
10.500 1.0440 0.03359 0.02524 0.0046 0.0525 1.0000
10.750 1.0502 0.03526 0.02692 0.0063 0.0491 1.0000
11.000 1.0593 0.03678 0.02869 0.0078 0.0449 1.0000
11.250 1.0647 0.03834 0.03035 0.0092 0.0414 1.0000
11.500 1.0675 0.04031 0.03235 0.0105 0.0385 1.0000
11.750 1.0726 0.04226 0.03460 0.0116 0.0353 1.0000
12.000 1.0748 0.04422 0.03669 0.0123 0.0325 1.0000
12.250 1.0749 0.04654 0.03907 0.0130 0.0308 1.0000
12.500 1.0736 0.04931 0.04201 0.0134 0.0288 1.0000
12.750 1.0721 0.05224 0.04520 0.0137 0.0270 1.0000
13.000 1.0687 0.05544 0.04859 0.0136 0.0257 1.0000
13.250 1.0641 0.05891 0.05223 0.0131 0.0248 1.0000
13.500 1.0579 0.06266 0.05611 0.0123 0.0240 1.0000
13.750 1.0507 0.06674 0.06034 0.0111 0.0235 1.0000
14.000 1.0416 0.07123 0.06493 0.0094 0.0229 1.0000
14.250 1.0304 0.07636 0.07017 0.0073 0.0225 1.0000
14.500 1.0157 0.08248 0.07654 0.0043 0.0222 1.0000
14.750 0.9994 0.08933 0.08361 0.0005 0.0221 1.0000
15.000 0.9810 0.09706 0.09154 -0.0040 0.0221 1.0000
15.250 0.9586 0.10627 0.10095 -0.0097 0.0221 1.0000
15.500 0.9401 0.11501 0.10983 -0.0149 0.0224 1.0000
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