NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 100,000 Max Cl/Cd: 43.46 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca24112-jf-100000-n5.txt Download as CSV file: xf-naca24112-jf-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 24112
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5962 0.08244 0.07727 -0.0205 1.0000 0.0383
-9.750 -0.6094 0.07689 0.07167 -0.0236 1.0000 0.0381
-9.500 -0.6249 0.07207 0.06678 -0.0246 1.0000 0.0380
-9.250 -0.6388 0.06758 0.06217 -0.0244 1.0000 0.0379
-9.000 -0.6491 0.06284 0.05725 -0.0238 1.0000 0.0378
-8.750 -0.6568 0.05798 0.05213 -0.0227 1.0000 0.0378
-8.500 -0.6625 0.05295 0.04676 -0.0211 1.0000 0.0379
-8.250 -0.6664 0.04779 0.04112 -0.0189 1.0000 0.0382
-8.000 -0.6571 0.04517 0.03831 -0.0174 1.0000 0.0389
-7.750 -0.6410 0.04397 0.03709 -0.0163 1.0000 0.0399
-7.500 -0.6286 0.04176 0.03468 -0.0147 1.0000 0.0411
-7.250 -0.6177 0.03886 0.03141 -0.0127 1.0000 0.0422
-7.000 -0.6059 0.03582 0.02794 -0.0105 1.0000 0.0431
-6.750 -0.5923 0.03295 0.02458 -0.0083 1.0000 0.0441
-6.500 -0.5759 0.03095 0.02226 -0.0065 1.0000 0.0456
-6.250 -0.5570 0.03002 0.02131 -0.0052 1.0000 0.0471
-6.000 -0.5384 0.02880 0.01995 -0.0036 1.0000 0.0489
-5.750 -0.5192 0.02726 0.01816 -0.0020 1.0000 0.0505
-5.500 -0.4994 0.02579 0.01636 -0.0004 1.0000 0.0524
-5.250 -0.4803 0.02487 0.01547 0.0010 1.0000 0.0544
-5.000 -0.4547 0.02405 0.01461 0.0011 0.9968 0.0570
-4.750 -0.4126 0.02276 0.01313 -0.0017 0.9855 0.0604
-4.500 -0.3722 0.02171 0.01207 -0.0043 0.9728 0.0644
-4.250 -0.3337 0.02086 0.01119 -0.0064 0.9575 0.0690
-4.000 -0.2967 0.01996 0.01024 -0.0081 0.9406 0.0738
-3.750 -0.2624 0.01925 0.00959 -0.0093 0.9205 0.0795
-3.500 -0.2299 0.01857 0.00885 -0.0099 0.8980 0.0857
-3.250 -0.1996 0.01797 0.00829 -0.0101 0.8741 0.0932
-3.000 -0.1725 0.01744 0.00770 -0.0096 0.8474 0.1013
-2.750 -0.1463 0.01703 0.00721 -0.0088 0.8207 0.1120
-2.500 -0.1219 0.01660 0.00675 -0.0077 0.7929 0.1248
-2.250 -0.0978 0.01622 0.00632 -0.0066 0.7653 0.1433
-2.000 -0.0742 0.01575 0.00590 -0.0054 0.7386 0.1773
-1.750 -0.0628 0.01370 0.00555 -0.0026 0.7146 0.5615
-1.500 -0.0339 0.01334 0.00593 -0.0005 0.6888 0.7909
-1.250 0.0021 0.01366 0.00618 -0.0004 0.6617 0.8626
-1.000 0.0384 0.01404 0.00633 -0.0008 0.6359 0.9007
-0.750 0.0767 0.01441 0.00648 -0.0019 0.6098 0.9285
-0.500 0.1284 0.01483 0.00662 -0.0057 0.5836 0.9530
-0.250 0.1822 0.01510 0.00663 -0.0105 0.5579 0.9723
0.000 0.2221 0.01519 0.00649 -0.0130 0.5369 0.9813
0.250 0.2591 0.01523 0.00633 -0.0150 0.5181 0.9870
0.500 0.2952 0.01530 0.00622 -0.0169 0.5008 0.9933
0.750 0.3325 0.01534 0.00610 -0.0191 0.4849 0.9984
1.000 0.3603 0.01540 0.00604 -0.0194 0.4714 1.0000
1.250 0.3842 0.01548 0.00602 -0.0189 0.4593 1.0000
1.500 0.4080 0.01559 0.00601 -0.0183 0.4485 1.0000
1.750 0.4316 0.01571 0.00603 -0.0177 0.4382 1.0000
2.000 0.4553 0.01584 0.00610 -0.0171 0.4283 1.0000
2.250 0.4786 0.01601 0.00615 -0.0164 0.4197 1.0000
2.500 0.5022 0.01616 0.00628 -0.0157 0.4104 1.0000
2.750 0.5255 0.01637 0.00637 -0.0150 0.4029 1.0000
3.000 0.5490 0.01655 0.00657 -0.0143 0.3942 1.0000
3.250 0.5721 0.01677 0.00670 -0.0135 0.3871 1.0000
3.500 0.5955 0.01699 0.00694 -0.0128 0.3792 1.0000
3.750 0.6185 0.01723 0.00713 -0.0120 0.3723 1.0000
4.000 0.6417 0.01749 0.00739 -0.0113 0.3652 1.0000
4.250 0.6647 0.01775 0.00764 -0.0105 0.3582 1.0000
4.500 0.6876 0.01804 0.00791 -0.0096 0.3521 1.0000
4.750 0.7105 0.01833 0.00824 -0.0088 0.3449 1.0000
5.000 0.7332 0.01863 0.00851 -0.0080 0.3388 1.0000
5.250 0.7560 0.01896 0.00890 -0.0071 0.3322 1.0000
5.500 0.7786 0.01927 0.00924 -0.0063 0.3256 1.0000
5.750 0.8012 0.01962 0.00957 -0.0054 0.3199 1.0000
6.000 0.8235 0.01997 0.01003 -0.0046 0.3129 1.0000
6.250 0.8459 0.02031 0.01037 -0.0037 0.3070 1.0000
6.500 0.8680 0.02070 0.01085 -0.0028 0.3004 1.0000
6.750 0.8901 0.02107 0.01128 -0.0019 0.2939 1.0000
7.000 0.9121 0.02145 0.01168 -0.0009 0.2881 1.0000
7.250 0.9335 0.02186 0.01224 0.0000 0.2810 1.0000
7.500 0.9553 0.02222 0.01259 0.0010 0.2750 1.0000
7.750 0.9762 0.02268 0.01321 0.0020 0.2677 1.0000
8.000 0.9974 0.02305 0.01364 0.0029 0.2610 1.0000
8.250 1.0180 0.02351 0.01421 0.0040 0.2539 1.0000
8.500 1.0385 0.02392 0.01469 0.0050 0.2465 1.0000
8.750 1.0586 0.02438 0.01528 0.0060 0.2390 1.0000
9.000 1.0783 0.02481 0.01579 0.0071 0.2311 1.0000
9.250 1.0974 0.02532 0.01643 0.0082 0.2228 1.0000
9.500 1.1160 0.02576 0.01692 0.0094 0.2148 1.0000
9.750 1.1338 0.02635 0.01768 0.0106 0.2054 1.0000
10.000 1.1508 0.02691 0.01829 0.0118 0.1968 1.0000
10.250 1.1667 0.02754 0.01903 0.0131 0.1873 1.0000
10.500 1.1817 0.02827 0.01991 0.0145 0.1776 1.0000
10.750 1.1949 0.02905 0.02075 0.0160 0.1684 1.0000
11.000 1.2062 0.02994 0.02171 0.0176 0.1587 1.0000
11.250 1.2160 0.03096 0.02287 0.0193 0.1490 1.0000
11.500 1.2219 0.03211 0.02408 0.0213 0.1403 1.0000
11.750 1.2234 0.03345 0.02548 0.0236 0.1323 1.0000
12.000 1.2245 0.03506 0.02721 0.0253 0.1244 1.0000
12.250 1.2215 0.03711 0.02928 0.0267 0.1179 1.0000
12.500 1.2196 0.03947 0.03180 0.0272 0.1108 1.0000
12.750 1.2124 0.04252 0.03487 0.0272 0.1057 1.0000
13.000 1.2069 0.04585 0.03838 0.0265 0.0999 1.0000
13.250 1.1969 0.04993 0.04252 0.0252 0.0956 1.0000
13.500 1.1867 0.05429 0.04698 0.0236 0.0917 1.0000
13.750 1.1755 0.05899 0.05182 0.0217 0.0878 1.0000
14.000 1.1622 0.06404 0.05693 0.0196 0.0847 1.0000
14.250 1.1496 0.06902 0.06196 0.0176 0.0818 1.0000
14.500 1.1372 0.07417 0.06727 0.0155 0.0786 1.0000
14.750 1.1246 0.07933 0.07251 0.0134 0.0757 1.0000
15.000 1.1142 0.08414 0.07733 0.0115 0.0732 1.0000
15.250 1.1045 0.08907 0.08234 0.0096 0.0705 1.0000
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