NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 100,000 Max Cl/Cd: 42.45 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca25112-jf-100000.txt Download as CSV file: xf-naca25112-jf-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 25112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4960 0.10794 0.10301 0.0015 1.0000 0.1153
-9.500 -0.5054 0.10401 0.09913 -0.0029 1.0000 0.1198
-9.250 -0.5509 0.09893 0.09415 -0.0155 1.0000 0.1216
-9.000 -0.5259 0.09374 0.08902 -0.0119 1.0000 0.1237
-8.750 -0.5026 0.09125 0.08652 -0.0078 1.0000 0.1272
-8.500 -0.5026 0.08739 0.08270 -0.0098 1.0000 0.1312
-8.250 -0.5278 0.08268 0.07800 -0.0156 1.0000 0.1356
-7.750 -0.5260 0.07438 0.06972 -0.0167 1.0000 0.1427
-7.500 -0.5237 0.07124 0.06654 -0.0171 1.0000 0.1498
-7.250 -0.5347 0.06693 0.06207 -0.0186 1.0000 0.1564
-7.000 -0.5177 0.06392 0.05916 -0.0171 1.0000 0.1613
-6.750 -0.5256 0.06083 0.05578 -0.0173 1.0000 0.1725
-6.500 -0.5088 0.05745 0.05254 -0.0160 1.0000 0.1767
-6.000 -0.5109 0.04331 0.03666 -0.0122 1.0000 0.1060
-5.750 -0.5011 0.04012 0.03343 -0.0100 1.0000 0.1043
-5.500 -0.4944 0.03731 0.03042 -0.0071 1.0000 0.1017
-5.250 -0.4898 0.03451 0.02727 -0.0038 1.0000 0.0986
-5.000 -0.4840 0.03249 0.02494 -0.0007 1.0000 0.0979
-4.750 -0.4454 0.03021 0.02228 -0.0034 0.9919 0.1015
-4.500 -0.3947 0.02757 0.01907 -0.0076 0.9801 0.1045
-4.250 -0.3434 0.02537 0.01660 -0.0123 0.9682 0.1110
-4.000 -0.2893 0.02378 0.01479 -0.0171 0.9559 0.1192
-3.750 -0.2407 0.02214 0.01308 -0.0208 0.9404 0.1283
-3.500 -0.1972 0.02093 0.01176 -0.0233 0.9214 0.1400
-3.250 -0.1613 0.02003 0.01082 -0.0241 0.8985 0.1528
-3.000 -0.1300 0.01908 0.00995 -0.0241 0.8762 0.1680
-2.750 -0.1036 0.01833 0.00923 -0.0229 0.8537 0.1864
-2.500 -0.0809 0.01757 0.00862 -0.0213 0.8306 0.2094
-2.250 -0.0598 0.01683 0.00806 -0.0193 0.8098 0.2465
-2.000 -0.0218 0.01473 0.00868 -0.0171 0.7926 0.8873
-1.750 0.1172 0.01607 0.00935 -0.0341 0.7685 0.9934
-1.500 0.1570 0.01595 0.00896 -0.0365 0.7469 1.0000
-1.250 0.1798 0.01595 0.00873 -0.0357 0.7288 1.0000
-1.000 0.2029 0.01597 0.00855 -0.0350 0.7122 1.0000
-0.750 0.2264 0.01601 0.00840 -0.0343 0.6969 1.0000
-0.500 0.2500 0.01606 0.00827 -0.0336 0.6830 1.0000
-0.250 0.2739 0.01613 0.00817 -0.0330 0.6695 1.0000
0.000 0.2984 0.01623 0.00815 -0.0326 0.6558 1.0000
0.250 0.3229 0.01635 0.00815 -0.0322 0.6434 1.0000
0.500 0.3471 0.01648 0.00813 -0.0315 0.6324 1.0000
0.750 0.3717 0.01661 0.00818 -0.0311 0.6206 1.0000
1.000 0.3962 0.01680 0.00829 -0.0306 0.6093 1.0000
1.250 0.4201 0.01697 0.00831 -0.0299 0.6001 1.0000
1.500 0.4445 0.01718 0.00851 -0.0295 0.5886 1.0000
1.750 0.4686 0.01742 0.00868 -0.0289 0.5790 1.0000
2.000 0.4925 0.01763 0.00883 -0.0282 0.5694 1.0000
2.250 0.5165 0.01792 0.00911 -0.0277 0.5595 1.0000
2.500 0.5403 0.01816 0.00923 -0.0269 0.5512 1.0000
2.750 0.5639 0.01849 0.00962 -0.0263 0.5410 1.0000
3.000 0.5878 0.01875 0.00974 -0.0254 0.5335 1.0000
3.250 0.6109 0.01913 0.01021 -0.0249 0.5232 1.0000
3.500 0.6347 0.01941 0.01039 -0.0240 0.5159 1.0000
3.750 0.6574 0.01982 0.01090 -0.0233 0.5058 1.0000
4.000 0.6811 0.02014 0.01113 -0.0224 0.4985 1.0000
4.250 0.7034 0.02056 0.01165 -0.0217 0.4887 1.0000
4.500 0.7269 0.02092 0.01195 -0.0208 0.4814 1.0000
4.750 0.7489 0.02136 0.01249 -0.0199 0.4717 1.0000
5.000 0.7722 0.02174 0.01283 -0.0190 0.4643 1.0000
5.250 0.7939 0.02219 0.01339 -0.0181 0.4548 1.0000
5.500 0.8169 0.02259 0.01378 -0.0172 0.4471 1.0000
5.750 0.8386 0.02303 0.01430 -0.0162 0.4378 1.0000
6.000 0.8609 0.02347 0.01478 -0.0153 0.4296 1.0000
6.250 0.8831 0.02386 0.01521 -0.0143 0.4206 1.0000
6.500 0.9045 0.02435 0.01578 -0.0132 0.4117 1.0000
6.750 0.9277 0.02461 0.01603 -0.0122 0.4031 1.0000
7.000 0.9476 0.02517 0.01673 -0.0111 0.3933 1.0000
7.250 0.9730 0.02525 0.01671 -0.0103 0.3852 1.0000
7.500 0.9913 0.02582 0.01747 -0.0089 0.3742 1.0000
7.750 1.0140 0.02607 0.01774 -0.0079 0.3649 1.0000
8.000 1.0366 0.02620 0.01787 -0.0068 0.3546 1.0000
8.250 1.0554 0.02661 0.01842 -0.0054 0.3432 1.0000
8.500 1.0774 0.02676 0.01858 -0.0043 0.3325 1.0000
8.750 1.1018 0.02668 0.01840 -0.0033 0.3215 1.0000
9.000 1.1190 0.02700 0.01888 -0.0017 0.3086 1.0000
9.250 1.1374 0.02727 0.01924 -0.0003 0.2956 1.0000
9.500 1.1559 0.02749 0.01952 0.0012 0.2823 1.0000
9.750 1.1737 0.02773 0.01979 0.0027 0.2684 1.0000
10.000 1.1899 0.02803 0.02013 0.0044 0.2538 1.0000
10.250 1.2042 0.02846 0.02060 0.0062 0.2382 1.0000
10.500 1.2162 0.02903 0.02119 0.0082 0.2220 1.0000
10.750 1.2259 0.02976 0.02192 0.0104 0.2056 1.0000
11.000 1.2329 0.03071 0.02283 0.0128 0.1894 1.0000
11.250 1.2371 0.03189 0.02397 0.0153 0.1742 1.0000
11.500 1.2384 0.03329 0.02536 0.0179 0.1604 1.0000
11.750 1.2358 0.03487 0.02695 0.0209 0.1487 1.0000
12.000 1.2340 0.03670 0.02878 0.0232 0.1384 1.0000
12.250 1.2350 0.03860 0.03059 0.0249 0.1291 1.0000
12.500 1.2339 0.04070 0.03274 0.0263 0.1209 1.0000
12.750 1.2340 0.04308 0.03518 0.0273 0.1137 1.0000
13.000 1.2399 0.04504 0.03702 0.0283 0.1067 1.0000
13.250 1.2374 0.04786 0.04005 0.0289 0.1016 1.0000
13.500 1.2410 0.05012 0.04230 0.0294 0.0962 1.0000
13.750 1.2461 0.05266 0.04489 0.0301 0.0917 1.0000
14.000 1.2405 0.05594 0.04840 0.0300 0.0883 1.0000
14.250 1.2485 0.05802 0.05042 0.0305 0.0841 1.0000
14.500 1.2514 0.06106 0.05355 0.0308 0.0811 1.0000
14.750 1.2392 0.06529 0.05807 0.0300 0.0794 1.0000
15.000 1.2276 0.06967 0.06268 0.0289 0.0777 1.0000
15.250 1.2161 0.07415 0.06735 0.0276 0.0761 1.0000
15.500 1.2150 0.07746 0.07073 0.0270 0.0738 1.0000
15.750 1.2206 0.08052 0.07376 0.0273 0.0714 1.0000
16.000 1.1948 0.08703 0.08054 0.0244 0.0712 1.0000
16.250 1.1663 0.09439 0.08816 0.0207 0.0712 1.0000
16.500 1.1343 0.10289 0.09688 0.0161 0.0714 1.0000
16.750 1.0993 0.11267 0.10686 0.0106 0.0717 1.0000
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