HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/9 AIRFOIL (hq109-il) Reynolds number: 100,000 Max Cl/Cd: 47.98 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq109-il-100000.txt Download as CSV file: xf-hq109-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5433 0.10314 0.09828 -0.0083 1.0000 0.1042
-9.250 -0.5590 0.09918 0.09442 -0.0141 1.0000 0.1085
-9.000 -0.5870 0.09446 0.08985 -0.0230 1.0000 0.1094
-8.750 -0.5462 0.09098 0.08629 -0.0139 1.0000 0.1154
-8.500 -0.5525 0.08703 0.08241 -0.0171 1.0000 0.1201
-8.250 -0.5922 0.08174 0.07720 -0.0275 1.0000 0.1225
-8.000 -0.5691 0.07789 0.07343 -0.0229 1.0000 0.1270
-7.750 -0.5726 0.07377 0.06931 -0.0255 1.0000 0.1330
-6.750 -0.5864 0.04553 0.03933 -0.0355 1.0000 0.0707
-6.500 -0.5704 0.04014 0.03322 -0.0336 1.0000 0.0560
-6.250 -0.5563 0.03562 0.02847 -0.0325 1.0000 0.0542
-6.000 -0.5400 0.03212 0.02454 -0.0310 1.0000 0.0531
-5.750 -0.5216 0.02938 0.02131 -0.0293 1.0000 0.0542
-5.500 -0.5029 0.02683 0.01830 -0.0277 1.0000 0.0581
-5.250 -0.4824 0.02456 0.01586 -0.0264 1.0000 0.0611
-5.000 -0.4608 0.02266 0.01375 -0.0248 1.0000 0.0658
-4.750 -0.4406 0.02095 0.01194 -0.0233 1.0000 0.0753
-4.500 -0.4208 0.01936 0.01036 -0.0216 1.0000 0.0889
-4.250 -0.4021 0.01811 0.00915 -0.0200 1.0000 0.1111
-4.000 -0.3845 0.01695 0.00819 -0.0183 1.0000 0.1398
-3.750 -0.3673 0.01575 0.00730 -0.0167 1.0000 0.1837
-3.500 -0.3566 0.01331 0.00646 -0.0145 1.0000 0.4262
-3.250 -0.3467 0.01285 0.00678 -0.0102 1.0000 0.6371
-3.000 -0.3337 0.01295 0.00695 -0.0064 1.0000 0.7100
-2.750 -0.3206 0.01308 0.00707 -0.0028 1.0000 0.7600
-2.500 -0.3082 0.01317 0.00714 0.0009 1.0000 0.7998
-2.250 -0.2967 0.01321 0.00717 0.0048 1.0000 0.8370
-2.000 -0.2853 0.01321 0.00717 0.0088 1.0000 0.8772
-1.750 -0.2616 0.01330 0.00722 0.0106 1.0000 0.9229
-1.500 -0.2020 0.01360 0.00729 0.0049 1.0000 0.9603
-1.250 -0.1206 0.01390 0.00733 -0.0055 1.0000 0.9859
-1.000 -0.0835 0.01384 0.00712 -0.0093 1.0000 1.0000
-0.750 -0.1021 0.01350 0.00674 -0.0040 1.0000 1.0000
-0.500 -0.0685 0.01371 0.00681 -0.0070 0.9940 1.0000
-0.250 -0.0225 0.01400 0.00699 -0.0118 0.9845 1.0000
0.000 0.0223 0.01429 0.00716 -0.0163 0.9745 1.0000
0.250 0.0680 0.01458 0.00738 -0.0207 0.9653 1.0000
0.500 0.1137 0.01484 0.00759 -0.0250 0.9562 1.0000
0.750 0.1527 0.01505 0.00779 -0.0279 0.9456 1.0000
1.000 0.1972 0.01523 0.00797 -0.0316 0.9350 1.0000
1.250 0.2546 0.01516 0.00795 -0.0372 0.9221 1.0000
1.500 0.3129 0.01489 0.00777 -0.0424 0.9077 1.0000
1.750 0.3561 0.01476 0.00771 -0.0450 0.8946 1.0000
2.000 0.3922 0.01470 0.00772 -0.0462 0.8809 1.0000
2.250 0.4238 0.01465 0.00774 -0.0463 0.8660 1.0000
2.500 0.4527 0.01460 0.00778 -0.0458 0.8500 1.0000
2.750 0.4799 0.01452 0.00776 -0.0447 0.8332 1.0000
3.000 0.5052 0.01442 0.00773 -0.0432 0.8152 1.0000
3.250 0.5276 0.01435 0.00773 -0.0412 0.7935 1.0000
3.500 0.5507 0.01420 0.00767 -0.0390 0.7704 1.0000
3.750 0.5736 0.01402 0.00754 -0.0368 0.7442 1.0000
4.000 0.5958 0.01386 0.00742 -0.0345 0.7125 1.0000
4.250 0.6179 0.01370 0.00727 -0.0322 0.6743 1.0000
4.500 0.6395 0.01364 0.00717 -0.0299 0.6247 1.0000
4.750 0.6602 0.01376 0.00720 -0.0276 0.5588 1.0000
5.000 0.6791 0.01424 0.00733 -0.0252 0.4734 1.0000
5.250 0.6965 0.01512 0.00774 -0.0232 0.3839 1.0000
5.500 0.7134 0.01626 0.00840 -0.0214 0.3049 1.0000
5.750 0.7300 0.01765 0.00936 -0.0198 0.2326 1.0000
6.000 0.7474 0.01904 0.01039 -0.0183 0.1700 1.0000
6.250 0.7657 0.02055 0.01165 -0.0169 0.1286 1.0000
6.500 0.7848 0.02233 0.01322 -0.0156 0.1012 1.0000
6.750 0.8059 0.02407 0.01499 -0.0144 0.0804 1.0000
7.000 0.8281 0.02615 0.01709 -0.0133 0.0667 1.0000
7.250 0.8509 0.02859 0.01964 -0.0123 0.0572 1.0000
7.500 0.8733 0.03097 0.02211 -0.0115 0.0509 1.0000
7.750 0.8929 0.03382 0.02541 -0.0102 0.0461 1.0000
8.000 0.9108 0.03708 0.02918 -0.0086 0.0441 1.0000
8.250 0.9244 0.04086 0.03351 -0.0068 0.0437 1.0000
8.500 0.9327 0.04520 0.03846 -0.0048 0.0441 1.0000
8.750 0.9359 0.04986 0.04363 -0.0029 0.0451 1.0000
9.000 0.9352 0.05469 0.04885 -0.0012 0.0464 1.0000
9.250 0.9320 0.05966 0.05410 0.0002 0.0477 1.0000
9.500 0.9338 0.06407 0.05877 0.0014 0.0508 1.0000
9.750 0.8856 0.07008 0.06527 0.0032 0.0543 1.0000
10.000 0.8586 0.07526 0.07060 0.0021 0.0556 1.0000
10.250 0.8328 0.08174 0.07716 -0.0016 0.0568 1.0000
10.500 0.8139 0.08904 0.08450 -0.0065 0.0586 1.0000
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Polar data table (+)
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