AH 80-140 (ah80140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-140 (ah80140-il) Reynolds number: 200,000 Max Cl/Cd: 70.92 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80140-il-200000.txt Download as CSV file: xf-ah80140-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-140
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2383 0.10238 0.09748 -0.0427 0.6492 0.0559
-9.750 -0.2545 0.09802 0.09319 -0.0482 0.6477 0.0588
-9.500 -0.2627 0.09329 0.08850 -0.0518 0.6459 0.0594
-9.250 -0.2378 0.09154 0.08667 -0.0488 0.6424 0.0605
-9.000 -0.2275 0.08918 0.08427 -0.0490 0.6400 0.0621
-8.750 -0.2257 0.08613 0.08125 -0.0507 0.6381 0.0648
-8.500 -0.2687 0.07917 0.07445 -0.0613 0.6375 0.0668
-8.250 -0.3039 0.07419 0.06939 -0.0653 0.6363 0.0670
-8.000 -0.2419 0.07422 0.06954 -0.0580 0.6326 0.0688
-7.750 -0.2384 0.07166 0.06701 -0.0583 0.6304 0.0701
-7.500 -0.2460 0.06846 0.06381 -0.0598 0.6285 0.0714
-7.250 -0.3007 0.06167 0.05642 -0.0665 0.6282 0.0761
-7.000 -0.2756 0.05765 0.05267 -0.0662 0.6258 0.0771
-6.750 -0.2586 0.05581 0.05085 -0.0654 0.6235 0.0784
-6.500 -0.2463 0.05371 0.04867 -0.0650 0.6214 0.0807
-6.250 -0.2496 0.04917 0.04369 -0.0658 0.6198 0.0875
-6.000 -0.2292 0.04754 0.04219 -0.0652 0.6176 0.0896
-5.750 -0.2407 0.03448 0.02760 -0.0627 0.6169 0.0600
-5.500 -0.2207 0.03190 0.02481 -0.0618 0.6145 0.0573
-5.250 -0.2015 0.02934 0.02186 -0.0606 0.6120 0.0566
-5.000 -0.1799 0.02745 0.01959 -0.0595 0.6096 0.0573
-4.750 -0.1567 0.02579 0.01757 -0.0585 0.6074 0.0578
-4.500 -0.1320 0.02448 0.01592 -0.0577 0.6055 0.0584
-4.250 -0.1068 0.02335 0.01450 -0.0570 0.6036 0.0595
-4.000 -0.0812 0.02259 0.01377 -0.0567 0.6015 0.0619
-3.750 -0.0552 0.02198 0.01311 -0.0563 0.5989 0.0648
-3.500 -0.0288 0.02137 0.01233 -0.0557 0.5964 0.0673
-3.250 -0.0030 0.02055 0.01162 -0.0554 0.5941 0.0705
-3.000 0.0233 0.02018 0.01120 -0.0549 0.5918 0.0751
-2.750 0.0487 0.01963 0.01071 -0.0544 0.5897 0.0805
-2.500 0.0748 0.01933 0.01035 -0.0539 0.5876 0.0865
-2.250 0.0998 0.01894 0.01002 -0.0533 0.5856 0.0944
-2.000 0.1246 0.01872 0.00980 -0.0526 0.5835 0.1037
-1.750 0.1487 0.01847 0.00969 -0.0520 0.5811 0.1164
-1.500 0.1727 0.01825 0.00961 -0.0514 0.5785 0.1366
-1.250 0.1946 0.01773 0.00949 -0.0505 0.5759 0.2030
-1.000 0.2060 0.01644 0.00950 -0.0478 0.5734 0.5186
-0.750 0.2214 0.01572 0.00974 -0.0443 0.5710 0.7898
-0.500 0.2675 0.01570 0.00982 -0.0467 0.5684 0.9073
-0.250 0.3271 0.01590 0.00986 -0.0523 0.5659 0.9560
0.000 0.3974 0.01626 0.01010 -0.0605 0.5626 0.9818
0.250 0.4656 0.01647 0.01024 -0.0688 0.5586 1.0000
0.500 0.4846 0.01665 0.01037 -0.0675 0.5554 1.0000
0.750 0.5046 0.01680 0.01045 -0.0662 0.5527 1.0000
1.000 0.5252 0.01697 0.01053 -0.0650 0.5504 1.0000
1.250 0.5466 0.01715 0.01063 -0.0638 0.5484 1.0000
1.500 0.5683 0.01744 0.01082 -0.0628 0.5465 1.0000
1.750 0.5867 0.01792 0.01135 -0.0615 0.5431 1.0000
2.000 0.6062 0.01833 0.01180 -0.0603 0.5390 1.0000
2.250 0.6283 0.01859 0.01202 -0.0594 0.5357 1.0000
2.500 0.6520 0.01875 0.01213 -0.0586 0.5332 1.0000
2.750 0.6762 0.01893 0.01225 -0.0578 0.5310 1.0000
3.000 0.7013 0.01912 0.01235 -0.0572 0.5290 1.0000
3.250 0.7227 0.01963 0.01288 -0.0563 0.5256 1.0000
3.500 0.7419 0.02021 0.01356 -0.0553 0.5204 1.0000
3.750 0.7657 0.02045 0.01380 -0.0546 0.5169 1.0000
4.000 0.7915 0.02052 0.01382 -0.0540 0.5143 1.0000
4.250 0.8177 0.02059 0.01384 -0.0535 0.5120 1.0000
4.500 0.8445 0.02074 0.01392 -0.0532 0.5101 1.0000
4.750 0.8616 0.02159 0.01493 -0.0520 0.5048 1.0000
5.000 0.8832 0.02203 0.01542 -0.0513 0.5002 1.0000
5.250 0.9091 0.02214 0.01552 -0.0508 0.4973 1.0000
5.500 0.9360 0.02214 0.01551 -0.0505 0.4948 1.0000
5.750 0.9650 0.02199 0.01530 -0.0502 0.4927 1.0000
6.000 0.9845 0.02255 0.01596 -0.0493 0.4873 1.0000
6.250 1.0071 0.02275 0.01624 -0.0485 0.4819 1.0000
6.500 1.0353 0.02249 0.01596 -0.0482 0.4786 1.0000
6.750 1.0661 0.02207 0.01548 -0.0482 0.4761 1.0000
7.000 1.0962 0.02182 0.01518 -0.0481 0.4735 1.0000
7.250 1.1101 0.02260 0.01619 -0.0466 0.4661 1.0000
7.500 1.1372 0.02245 0.01606 -0.0463 0.4624 1.0000
7.750 1.1670 0.02216 0.01575 -0.0462 0.4598 1.0000
8.000 1.1990 0.02176 0.01529 -0.0464 0.4574 1.0000
8.250 1.2118 0.02247 0.01626 -0.0447 0.4495 1.0000
8.500 1.2416 0.02191 0.01569 -0.0445 0.4451 1.0000
8.750 1.2739 0.02135 0.01508 -0.0447 0.4419 1.0000
9.000 1.2898 0.02190 0.01583 -0.0433 0.4351 1.0000
9.250 1.3167 0.02150 0.01546 -0.0429 0.4294 1.0000
9.500 1.3442 0.02091 0.01488 -0.0424 0.4224 1.0000
9.750 1.3672 0.02056 0.01460 -0.0414 0.4134 1.0000
10.000 1.3885 0.02037 0.01449 -0.0403 0.4034 1.0000
10.250 1.4134 0.02001 0.01408 -0.0396 0.3939 1.0000
10.500 1.4305 0.02017 0.01432 -0.0381 0.3818 1.0000
10.750 1.4464 0.02047 0.01469 -0.0365 0.3692 1.0000
11.000 1.4605 0.02088 0.01512 -0.0348 0.3559 1.0000
11.250 1.4720 0.02144 0.01569 -0.0328 0.3427 1.0000
11.500 1.4780 0.02217 0.01642 -0.0302 0.3293 1.0000
11.750 1.4789 0.02317 0.01739 -0.0273 0.3162 1.0000
12.000 1.4758 0.02476 0.01901 -0.0251 0.3025 1.0000
12.250 1.4708 0.02704 0.02133 -0.0242 0.2879 1.0000
12.500 1.4642 0.02984 0.02412 -0.0238 0.2725 1.0000
12.750 1.4565 0.03289 0.02715 -0.0236 0.2576 1.0000
13.000 1.4476 0.03613 0.03036 -0.0234 0.2428 1.0000
13.250 1.4384 0.03940 0.03361 -0.0231 0.2287 1.0000
13.500 1.4290 0.04271 0.03689 -0.0229 0.2155 1.0000
13.750 1.4197 0.04602 0.04016 -0.0227 0.2033 1.0000
14.000 1.4098 0.04944 0.04354 -0.0225 0.1911 1.0000
14.250 1.4001 0.05294 0.04702 -0.0224 0.1790 1.0000
14.500 1.3907 0.05665 0.05069 -0.0226 0.1661 1.0000
14.750 1.3803 0.06057 0.05456 -0.0229 0.1534 1.0000
15.000 1.3687 0.06481 0.05876 -0.0234 0.1392 1.0000
15.250 1.3576 0.06911 0.06305 -0.0240 0.1238 1.0000
15.500 1.3433 0.07388 0.06774 -0.0247 0.1088 1.0000
15.750 1.3294 0.07871 0.07249 -0.0255 0.0957 1.0000
16.000 1.3160 0.08355 0.07725 -0.0263 0.0849 1.0000
16.250 1.3045 0.08821 0.08186 -0.0272 0.0765 1.0000
16.500 1.2967 0.09237 0.08596 -0.0279 0.0713 1.0000
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