AH 79-K-143/18 (ah79k143-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-143/18 (ah79k143-il) Reynolds number: 100,000 Max Cl/Cd: 37.84 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k143-il-100000-n5.txt Download as CSV file: xf-ah79k143-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-143/18
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2805 0.09827 0.09254 -0.0879 0.8746 0.0290
-11.250 -0.2821 0.09285 0.08716 -0.0911 0.8735 0.0287
-11.000 -0.2855 0.08709 0.08145 -0.0949 0.8724 0.0284
-10.750 -0.2923 0.08045 0.07485 -0.0995 0.8712 0.0278
-10.500 -0.3118 0.07007 0.06449 -0.1080 0.8695 0.0272
-10.250 -0.3511 0.06016 0.05439 -0.1140 0.8672 0.0261
-9.750 -0.4041 0.05069 0.04441 -0.1118 0.8627 0.0256
-9.500 -0.4199 0.04806 0.04153 -0.1081 0.8603 0.0256
-9.250 -0.4275 0.04551 0.03872 -0.1050 0.8579 0.0256
-9.000 -0.4292 0.04325 0.03620 -0.1023 0.8555 0.0259
-8.750 -0.4266 0.04113 0.03381 -0.0998 0.8535 0.0264
-8.500 -0.4215 0.03899 0.03134 -0.0974 0.8517 0.0267
-8.250 -0.4135 0.03710 0.02913 -0.0951 0.8497 0.0274
-8.000 -0.4044 0.03537 0.02710 -0.0927 0.8473 0.0285
-7.750 -0.3927 0.03376 0.02505 -0.0905 0.8449 0.0305
-7.500 -0.3769 0.03218 0.02318 -0.0890 0.8429 0.0318
-7.250 -0.3588 0.03111 0.02201 -0.0879 0.8409 0.0335
-7.000 -0.3383 0.02998 0.02067 -0.0869 0.8389 0.0356
-6.750 -0.3158 0.02899 0.01936 -0.0861 0.8370 0.0384
-6.500 -0.2977 0.02803 0.01839 -0.0849 0.8344 0.0411
-6.250 -0.2781 0.02726 0.01757 -0.0838 0.8319 0.0441
-6.000 -0.2567 0.02665 0.01677 -0.0827 0.8293 0.0488
-5.750 -0.2366 0.02593 0.01610 -0.0817 0.8271 0.0528
-5.500 -0.2148 0.02539 0.01543 -0.0808 0.8251 0.0582
-5.250 -0.2009 0.02495 0.01503 -0.0787 0.8216 0.0642
-5.000 -0.1838 0.02460 0.01462 -0.0769 0.8183 0.0728
-4.750 -0.1656 0.02419 0.01423 -0.0754 0.8154 0.0845
-4.500 -0.1450 0.02385 0.01391 -0.0743 0.8132 0.1027
-4.250 -0.1336 0.02364 0.01382 -0.0718 0.8088 0.1231
-4.000 -0.1173 0.02335 0.01369 -0.0701 0.8053 0.1571
-3.750 -0.0985 0.02296 0.01353 -0.0688 0.8025 0.2112
-3.500 -0.0825 0.02241 0.01342 -0.0670 0.7999 0.3080
-3.000 -0.0237 0.02227 0.01514 -0.0648 0.7940 0.7415
-2.750 -0.0025 0.02296 0.01571 -0.0626 0.7908 0.7852
-2.500 0.0108 0.02346 0.01606 -0.0593 0.7879 0.8167
-2.250 0.0167 0.02406 0.01660 -0.0550 0.7826 0.8387
-2.000 0.0362 0.02462 0.01704 -0.0529 0.7785 0.8583
-1.750 0.0633 0.02513 0.01742 -0.0520 0.7757 0.8791
-1.500 0.1503 0.02578 0.01785 -0.0619 0.7758 0.9048
-1.250 0.2007 0.02584 0.01777 -0.0661 0.7742 0.9155
-1.000 0.2138 0.02603 0.01789 -0.0639 0.7689 0.9247
-0.750 0.2455 0.02604 0.01781 -0.0652 0.7645 0.9287
-0.500 0.2735 0.02599 0.01768 -0.0656 0.7611 0.9335
-0.250 0.2992 0.02591 0.01751 -0.0654 0.7586 0.9384
0.000 0.3212 0.02611 0.01770 -0.0653 0.7519 0.9434
0.250 0.3441 0.02612 0.01767 -0.0648 0.7476 0.9489
0.500 0.3760 0.02601 0.01750 -0.0659 0.7450 0.9523
0.750 0.4006 0.02616 0.01764 -0.0661 0.7394 0.9568
1.000 0.4182 0.02626 0.01774 -0.0648 0.7339 0.9622
1.250 0.4525 0.02612 0.01758 -0.0663 0.7311 0.9645
1.750 0.4964 0.02637 0.01786 -0.0656 0.7197 0.9729
2.000 0.5309 0.02617 0.01766 -0.0671 0.7168 0.9750
2.250 0.5521 0.02642 0.01796 -0.0668 0.7100 0.9789
2.500 0.5759 0.02644 0.01801 -0.0666 0.7049 0.9823
2.750 0.6099 0.02619 0.01779 -0.0679 0.7022 0.9841
3.000 0.6272 0.02659 0.01827 -0.0671 0.6937 0.9881
3.250 0.6556 0.02643 0.01816 -0.0675 0.6895 0.9902
3.500 0.6894 0.02608 0.01787 -0.0686 0.6870 0.9917
3.750 0.7052 0.02658 0.01846 -0.0677 0.6771 0.9958
4.000 0.7370 0.02625 0.01823 -0.0684 0.6738 0.9976
4.500 0.7689 0.02643 0.01856 -0.0649 0.6602 1.0000
4.750 0.7855 0.02626 0.01846 -0.0628 0.6552 1.0000
5.000 0.7876 0.02653 0.01881 -0.0586 0.6463 1.0000
5.250 0.8145 0.02595 0.01832 -0.0579 0.6432 1.0000
5.500 0.8030 0.02653 0.01894 -0.0516 0.6318 1.0000
5.750 0.8319 0.02591 0.01843 -0.0511 0.6286 1.0000
6.000 0.8155 0.02654 0.01909 -0.0440 0.6169 1.0000
6.250 0.8474 0.02576 0.01846 -0.0439 0.6132 1.0000
6.500 0.8352 0.02631 0.01905 -0.0376 0.6012 1.0000
6.750 0.8698 0.02540 0.01827 -0.0376 0.5968 1.0000
7.000 0.8633 0.02580 0.01872 -0.0323 0.5846 1.0000
7.250 0.8657 0.02595 0.01894 -0.0282 0.5730 1.0000
7.500 0.8823 0.02552 0.01862 -0.0257 0.5612 1.0000
7.750 0.8957 0.02505 0.01819 -0.0227 0.5430 1.0000
8.000 0.9096 0.02450 0.01760 -0.0196 0.5160 1.0000
8.250 0.9162 0.02446 0.01747 -0.0159 0.4832 1.0000
8.500 0.9263 0.02448 0.01731 -0.0129 0.4426 1.0000
8.750 0.9298 0.02512 0.01780 -0.0096 0.4020 1.0000
9.000 0.9302 0.02605 0.01845 -0.0062 0.3486 1.0000
9.250 0.9238 0.02756 0.01953 -0.0026 0.2850 1.0000
9.500 0.9166 0.02938 0.02096 0.0006 0.2238 1.0000
9.750 0.9066 0.03163 0.02273 0.0037 0.1570 1.0000
10.000 0.9007 0.03383 0.02452 0.0062 0.1017 1.0000
10.500 0.8998 0.03781 0.02813 0.0101 0.0584 1.0000
10.750 0.9029 0.03962 0.02998 0.0115 0.0506 1.0000
11.000 0.9073 0.04139 0.03182 0.0128 0.0451 1.0000
11.250 0.9122 0.04315 0.03365 0.0139 0.0417 1.0000
11.500 0.9136 0.04527 0.03580 0.0152 0.0388 1.0000
11.750 0.9198 0.04708 0.03775 0.0162 0.0367 1.0000
12.000 0.9261 0.04890 0.03967 0.0171 0.0345 1.0000
12.250 0.9328 0.05073 0.04156 0.0179 0.0327 1.0000
12.500 0.9388 0.05266 0.04348 0.0187 0.0307 1.0000
12.750 0.9503 0.05418 0.04516 0.0194 0.0291 1.0000
13.000 0.9629 0.05566 0.04675 0.0202 0.0280 1.0000
13.250 0.9764 0.05715 0.04833 0.0209 0.0269 1.0000
13.500 0.9905 0.05870 0.04996 0.0215 0.0259 1.0000
13.750 1.0053 0.06028 0.05161 0.0221 0.0253 1.0000
14.000 1.0217 0.06196 0.05336 0.0226 0.0246 1.0000
14.250 1.0382 0.06400 0.05554 0.0231 0.0241 1.0000
14.500 1.0428 0.06671 0.05857 0.0236 0.0234 1.0000
14.750 1.0453 0.06963 0.06177 0.0239 0.0228 1.0000
15.000 1.0452 0.07280 0.06521 0.0240 0.0223 1.0000
15.250 1.0419 0.07623 0.06888 0.0238 0.0217 1.0000
15.500 1.0368 0.08009 0.07298 0.0235 0.0213 1.0000
15.750 1.0298 0.08416 0.07729 0.0228 0.0210 1.0000
16.000 1.0205 0.08869 0.08205 0.0217 0.0208 1.0000
16.250 1.0077 0.09395 0.08758 0.0202 0.0209 1.0000
16.500 0.9922 0.09978 0.09364 0.0181 0.0208 1.0000
16.750 0.9751 0.10611 0.10021 0.0153 0.0209 1.0000
17.000 0.9546 0.11346 0.10780 0.0116 0.0209 1.0000
17.250 0.9314 0.12193 0.11650 0.0070 0.0213 1.0000
17.500 0.9050 0.13184 0.12662 0.0010 0.0214 1.0000
17.750 0.8713 0.14487 0.13982 -0.0071 0.0220 1.0000
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