NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il) Reynolds number: 50,000 Max Cl/Cd: 30.76 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h10-il-50000.txt Download as CSV file: xf-n5h10-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5288 0.13128 0.12485 0.0046 1.0000 0.1736
-10.500 -0.5111 0.12574 0.11932 0.0051 1.0000 0.1818
-10.250 -0.5239 0.12423 0.11792 0.0017 1.0000 0.1884
-10.000 -0.5043 0.11885 0.11252 0.0025 1.0000 0.1991
-9.750 -0.5006 0.11512 0.10882 0.0014 1.0000 0.2082
-9.500 -0.5138 0.11340 0.10721 -0.0015 1.0000 0.2172
-9.250 -0.5046 0.10943 0.10328 -0.0016 1.0000 0.2312
-9.000 -0.5001 0.10584 0.09975 -0.0020 1.0000 0.2458
-8.750 -0.4998 0.10256 0.09655 -0.0027 1.0000 0.2608
-8.500 -0.5019 0.09946 0.09354 -0.0035 1.0000 0.2759
-8.000 -0.4802 0.09172 0.08588 -0.0019 1.0000 0.3190
-7.750 -0.4629 0.08771 0.08189 -0.0003 1.0000 0.3456
-7.500 -0.4554 0.08456 0.07880 0.0010 1.0000 0.3756
-7.250 -0.4623 0.08241 0.07677 0.0026 1.0000 0.4080
-7.000 -0.4389 0.07927 0.07360 0.0071 1.0000 0.4668
-6.750 -0.3930 0.07493 0.06917 0.0110 1.0000 0.5377
-5.750 -0.2736 0.06075 0.05487 0.0126 1.0000 0.7331
-5.500 -0.3466 0.05983 0.05433 0.0140 1.0000 0.6396
-5.250 -0.4028 0.05959 0.05436 0.0198 1.0000 0.6102
-5.000 -0.4529 0.05935 0.05432 0.0275 1.0000 0.6030
-4.750 -0.4995 0.05867 0.05381 0.0347 1.0000 0.6016
-4.500 -0.5471 0.05737 0.05265 0.0406 1.0000 0.5995
-4.250 -0.5406 0.04678 0.03965 0.0026 1.0000 0.2134
-4.000 -0.5181 0.04285 0.03482 0.0032 1.0000 0.1702
-3.750 -0.4989 0.03996 0.03130 0.0047 1.0000 0.1538
-3.500 -0.4786 0.03777 0.02834 0.0064 1.0000 0.1439
-3.250 -0.4593 0.03592 0.02601 0.0079 1.0000 0.1444
-3.000 -0.4384 0.03410 0.02379 0.0092 1.0000 0.1442
-2.750 -0.4156 0.03237 0.02171 0.0102 1.0000 0.1434
-2.500 -0.3924 0.03107 0.02001 0.0112 1.0000 0.1448
-2.250 -0.3695 0.02968 0.01859 0.0117 1.0000 0.1523
-2.000 -0.3425 0.02870 0.01730 0.0121 1.0000 0.1580
-1.750 -0.1173 0.02436 0.01609 -0.0181 1.0000 1.0000
-1.500 -0.1068 0.02463 0.01578 -0.0156 1.0000 1.0000
-1.250 -0.0973 0.02489 0.01570 -0.0132 1.0000 1.0000
-1.000 -0.0874 0.02516 0.01569 -0.0111 0.9999 1.0000
-0.750 -0.0604 0.02559 0.01579 -0.0123 0.9953 1.0000
-0.500 -0.0365 0.02602 0.01598 -0.0129 0.9910 1.0000
-0.250 -0.0152 0.02647 0.01622 -0.0131 0.9873 1.0000
0.000 0.0089 0.02704 0.01661 -0.0138 0.9835 1.0000
0.250 0.0271 0.02750 0.01692 -0.0133 0.9800 1.0000
0.500 0.0436 0.02797 0.01725 -0.0126 0.9769 1.0000
0.750 0.0616 0.02851 0.01768 -0.0122 0.9738 1.0000
1.000 0.0824 0.02917 0.01824 -0.0122 0.9706 1.0000
1.250 0.0985 0.02976 0.01875 -0.0115 0.9680 1.0000
1.500 0.1112 0.03027 0.01919 -0.0101 0.9653 1.0000
1.750 0.1262 0.03087 0.01973 -0.0092 0.9622 1.0000
2.000 0.1475 0.03166 0.02048 -0.0095 0.9579 1.0000
2.250 0.1717 0.03249 0.02128 -0.0103 0.9498 1.0000
2.500 0.2069 0.03357 0.02238 -0.0130 0.9376 1.0000
2.750 0.2422 0.03469 0.02353 -0.0156 0.9250 1.0000
3.000 0.2639 0.03556 0.02443 -0.0159 0.9147 1.0000
3.250 0.2825 0.03649 0.02539 -0.0156 0.9056 1.0000
3.500 0.3092 0.03765 0.02663 -0.0167 0.8953 1.0000
3.750 0.3400 0.03895 0.02803 -0.0185 0.8840 1.0000
4.000 0.3534 0.03988 0.02903 -0.0173 0.8727 1.0000
4.250 0.3734 0.04104 0.03029 -0.0172 0.8600 1.0000
4.500 0.3973 0.04233 0.03170 -0.0177 0.8456 1.0000
4.750 0.4225 0.04367 0.03322 -0.0184 0.8305 1.0000
5.000 0.4524 0.04513 0.03486 -0.0196 0.8138 1.0000
5.250 0.4662 0.04637 0.03623 -0.0185 0.7977 1.0000
5.500 0.4873 0.04755 0.03759 -0.0181 0.7772 1.0000
5.750 0.5443 0.04818 0.03864 -0.0208 0.7441 1.0000
6.000 0.5804 0.04801 0.03878 -0.0200 0.7090 1.0000
6.250 0.8055 0.02898 0.02159 -0.0177 0.5835 1.0000
6.500 0.7954 0.02586 0.01668 -0.0031 0.2897 1.0000
6.750 0.7796 0.02849 0.01836 0.0026 0.2135 1.0000
7.000 0.7770 0.03055 0.01987 0.0069 0.1813 1.0000
7.250 0.7995 0.03252 0.02153 0.0093 0.1561 1.0000
7.500 0.8500 0.03503 0.02374 0.0084 0.1329 1.0000
7.750 0.8843 0.03735 0.02630 0.0088 0.1238 1.0000
8.000 0.9077 0.03999 0.02919 0.0100 0.1161 1.0000
8.250 0.9273 0.04259 0.03215 0.0116 0.1117 1.0000
8.500 0.9455 0.04570 0.03560 0.0133 0.1098 1.0000
8.750 0.9637 0.04928 0.03931 0.0145 0.1072 1.0000
9.000 0.9720 0.05286 0.04323 0.0166 0.1055 1.0000
9.250 0.9742 0.05598 0.04682 0.0192 0.1048 1.0000
9.500 0.9776 0.05981 0.05099 0.0213 0.1052 1.0000
9.750 0.9774 0.06352 0.05511 0.0236 0.1070 1.0000
10.000 0.9495 0.06663 0.05882 0.0272 0.1103 1.0000
10.250 0.9264 0.07060 0.06310 0.0295 0.1130 1.0000
10.500 0.9047 0.07449 0.06713 0.0313 0.1152 1.0000
10.750 0.8887 0.07889 0.07161 0.0320 0.1174 1.0000
11.000 0.8782 0.08379 0.07662 0.0319 0.1211 1.0000
11.500 0.7826 0.09958 0.09244 0.0223 0.1315 1.0000
11.750 0.7637 0.11039 0.10321 0.0163 0.1475 1.0000
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Polar data table (+)
Polar graphs
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