NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il) Reynolds number: 200,000 Max Cl/Cd: 65.83 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h10-il-200000.txt Download as CSV file: xf-n5h10-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-10 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4035 0.09118 0.08833 -0.0160 0.9627 0.0419
-9.250 -0.4005 0.08601 0.08313 -0.0198 0.9437 0.0431
-9.000 -0.4035 0.08099 0.07808 -0.0235 0.9313 0.0445
-8.750 -0.4144 0.07591 0.07300 -0.0282 0.9207 0.0455
-8.500 -0.4278 0.07108 0.06812 -0.0323 0.9111 0.0457
-8.250 -0.4432 0.06714 0.06412 -0.0339 0.9011 0.0459
-8.000 -0.4600 0.06377 0.06061 -0.0335 0.8918 0.0462
-7.500 -0.4747 0.05663 0.05306 -0.0319 0.8762 0.0466
-7.250 -0.4819 0.04904 0.04540 -0.0313 0.8709 0.0475
-7.000 -0.4710 0.04500 0.04143 -0.0309 0.8646 0.0488
-6.750 -0.4632 0.04198 0.03834 -0.0298 0.8583 0.0504
-6.500 -0.4550 0.03870 0.03494 -0.0289 0.8522 0.0529
-6.250 -0.4481 0.03758 0.03310 -0.0260 0.8444 0.0595
-6.000 -0.4599 0.04443 0.03959 -0.0275 0.8537 0.0619
-5.750 -0.4437 0.04215 0.03731 -0.0267 0.8471 0.0648
-5.500 -0.4263 0.04382 0.03819 -0.0233 0.8410 0.0734
-5.250 -0.4146 0.03713 0.03164 -0.0234 0.8348 0.0767
-5.000 -0.3965 0.03519 0.02959 -0.0221 0.8295 0.0815
-4.750 -0.3792 0.03299 0.02704 -0.0207 0.8235 0.0916
-4.500 -0.3609 0.03137 0.02521 -0.0195 0.8180 0.1055
-4.250 -0.3298 0.02503 0.01770 -0.0155 0.8145 0.0540
-4.000 -0.3029 0.02262 0.01487 -0.0146 0.8086 0.0518
-3.750 -0.2772 0.02154 0.01358 -0.0139 0.8036 0.0550
-3.500 -0.2505 0.02034 0.01213 -0.0131 0.7995 0.0566
-3.250 -0.2221 0.01934 0.01095 -0.0130 0.7937 0.0582
-3.000 -0.1951 0.01816 0.00967 -0.0127 0.7895 0.0619
-2.750 -0.1694 0.01733 0.00883 -0.0121 0.7862 0.0648
-2.500 -0.1427 0.01671 0.00823 -0.0120 0.7804 0.0679
-2.250 -0.1174 0.01631 0.00777 -0.0114 0.7759 0.0727
-2.000 -0.0949 0.01560 0.00708 -0.0102 0.7726 0.0776
-1.750 -0.0704 0.01524 0.00674 -0.0097 0.7674 0.0846
-1.500 -0.0468 0.01481 0.00634 -0.0089 0.7631 0.0995
-1.250 -0.0472 0.01248 0.00592 -0.0041 0.7596 0.5442
-1.000 0.2097 0.01343 0.00749 -0.0445 0.7619 1.0000
-0.750 0.2329 0.01341 0.00738 -0.0437 0.7585 1.0000
-0.500 0.2576 0.01344 0.00738 -0.0435 0.7533 1.0000
-0.250 0.2815 0.01343 0.00731 -0.0430 0.7484 1.0000
0.000 0.3047 0.01339 0.00721 -0.0421 0.7447 1.0000
0.250 0.3292 0.01343 0.00724 -0.0418 0.7398 1.0000
0.500 0.3535 0.01345 0.00724 -0.0414 0.7348 1.0000
0.750 0.3769 0.01341 0.00717 -0.0406 0.7310 1.0000
1.000 0.4011 0.01345 0.00721 -0.0401 0.7267 1.0000
1.250 0.4258 0.01353 0.00732 -0.0399 0.7218 1.0000
1.500 0.4497 0.01353 0.00733 -0.0392 0.7180 1.0000
1.750 0.4732 0.01351 0.00729 -0.0384 0.7150 1.0000
2.000 0.4978 0.01360 0.00746 -0.0381 0.7084 1.0000
2.250 0.5211 0.01346 0.00731 -0.0371 0.7029 1.0000
2.500 0.5435 0.01319 0.00706 -0.0358 0.6924 1.0000
2.750 0.5655 0.01277 0.00662 -0.0341 0.6800 1.0000
3.000 0.5879 0.01245 0.00627 -0.0326 0.6682 1.0000
3.250 0.6111 0.01227 0.00608 -0.0315 0.6591 1.0000
3.500 0.6342 0.01212 0.00597 -0.0304 0.6467 1.0000
3.750 0.6575 0.01202 0.00595 -0.0294 0.6350 1.0000
4.000 0.6806 0.01191 0.00587 -0.0284 0.6212 1.0000
4.250 0.7033 0.01177 0.00576 -0.0272 0.6034 1.0000
4.500 0.7261 0.01170 0.00576 -0.0261 0.5831 1.0000
4.750 0.7484 0.01164 0.00574 -0.0249 0.5530 1.0000
5.000 0.7695 0.01169 0.00570 -0.0235 0.4899 1.0000
5.250 0.7791 0.01338 0.00624 -0.0212 0.2786 1.0000
5.500 0.7863 0.01580 0.00759 -0.0194 0.0964 1.0000
5.750 0.8026 0.01677 0.00846 -0.0179 0.0717 1.0000
6.000 0.8190 0.01755 0.00926 -0.0163 0.0622 1.0000
6.250 0.8339 0.01837 0.01008 -0.0145 0.0560 1.0000
6.500 0.8465 0.01932 0.01110 -0.0123 0.0526 1.0000
6.750 0.8594 0.02014 0.01198 -0.0100 0.0494 1.0000
7.000 0.8697 0.02107 0.01290 -0.0075 0.0457 1.0000
7.250 0.8768 0.02261 0.01444 -0.0043 0.0432 1.0000
7.500 0.8897 0.02360 0.01554 -0.0017 0.0420 1.0000
7.750 0.9033 0.02469 0.01673 0.0007 0.0402 1.0000
8.000 0.9158 0.02571 0.01782 0.0032 0.0375 1.0000
8.250 0.9297 0.02700 0.01916 0.0054 0.0359 1.0000
8.500 0.9477 0.02899 0.02124 0.0071 0.0345 1.0000
8.750 0.9664 0.03167 0.02411 0.0086 0.0338 1.0000
9.000 0.9803 0.03446 0.02718 0.0107 0.0336 1.0000
9.250 0.9839 0.03765 0.03074 0.0139 0.0325 1.0000
9.500 0.9900 0.03950 0.03289 0.0168 0.0321 1.0000
9.750 0.9939 0.04238 0.03609 0.0196 0.0320 1.0000
10.000 1.0077 0.04578 0.03966 0.0212 0.0336 1.0000
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Polar data table (+)
Polar graphs
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