NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 100,000 Max Cl/Cd: 46.71 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca25112-jf-100000-n5.txt Download as CSV file: xf-naca25112-jf-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5519 0.08822 0.08319 -0.0127 1.0000 0.0399
-9.500 -0.5693 0.07973 0.07473 -0.0202 1.0000 0.0394
-9.250 -0.5942 0.07202 0.06694 -0.0245 1.0000 0.0389
-9.000 -0.6162 0.06516 0.05992 -0.0258 1.0000 0.0386
-8.750 -0.6256 0.05988 0.05445 -0.0258 1.0000 0.0390
-8.500 -0.6290 0.05537 0.04972 -0.0251 1.0000 0.0397
-8.250 -0.6321 0.05048 0.04451 -0.0239 1.0000 0.0406
-8.000 -0.6342 0.04536 0.03892 -0.0219 1.0000 0.0416
-7.750 -0.6330 0.04052 0.03352 -0.0196 1.0000 0.0423
-7.500 -0.6279 0.03618 0.02846 -0.0170 1.0000 0.0432
-7.250 -0.6111 0.03458 0.02678 -0.0157 1.0000 0.0442
-7.000 -0.5929 0.03351 0.02565 -0.0145 1.0000 0.0456
-6.750 -0.5763 0.03190 0.02382 -0.0129 1.0000 0.0474
-6.500 -0.5607 0.02979 0.02131 -0.0109 1.0000 0.0492
-6.250 -0.5439 0.02783 0.01894 -0.0090 1.0000 0.0507
-6.000 -0.5262 0.02696 0.01811 -0.0075 1.0000 0.0523
-5.750 -0.4897 0.02584 0.01686 -0.0097 0.9874 0.0554
-5.500 -0.4514 0.02427 0.01492 -0.0117 0.9720 0.0587
-5.250 -0.4142 0.02320 0.01386 -0.0138 0.9544 0.0618
-5.000 -0.3784 0.02231 0.01284 -0.0154 0.9339 0.0661
-4.750 -0.3435 0.02127 0.01168 -0.0165 0.9122 0.0701
-4.500 -0.3113 0.02060 0.01099 -0.0173 0.8888 0.0749
-4.250 -0.2818 0.01994 0.01014 -0.0171 0.8637 0.0802
-4.000 -0.2553 0.01931 0.00954 -0.0166 0.8392 0.0855
-3.750 -0.2297 0.01884 0.00892 -0.0157 0.8143 0.0923
-3.500 -0.2055 0.01833 0.00840 -0.0146 0.7912 0.0991
-3.250 -0.1810 0.01793 0.00789 -0.0135 0.7692 0.1079
-3.000 -0.1570 0.01754 0.00746 -0.0125 0.7478 0.1179
-2.750 -0.1328 0.01717 0.00706 -0.0115 0.7279 0.1301
-2.500 -0.1084 0.01683 0.00669 -0.0106 0.7092 0.1460
-2.250 -0.0838 0.01651 0.00635 -0.0097 0.6915 0.1673
-2.000 -0.0593 0.01614 0.00605 -0.0090 0.6751 0.1999
-1.750 -0.0356 0.01559 0.00575 -0.0082 0.6597 0.2691
-1.500 -0.0093 0.01376 0.00605 -0.0065 0.6456 0.7904
-1.250 0.0353 0.01419 0.00641 -0.0080 0.6304 0.8852
-1.000 0.0713 0.01457 0.00658 -0.0086 0.6166 0.9242
-0.750 0.1225 0.01493 0.00672 -0.0124 0.6018 0.9499
-0.500 0.1731 0.01518 0.00675 -0.0165 0.5876 0.9714
-0.250 0.2394 0.01529 0.00665 -0.0241 0.5728 0.9932
0.000 0.2811 0.01527 0.00645 -0.0271 0.5610 1.0000
0.250 0.3055 0.01529 0.00633 -0.0266 0.5511 1.0000
0.500 0.3302 0.01532 0.00627 -0.0262 0.5408 1.0000
0.750 0.3547 0.01538 0.00618 -0.0257 0.5322 1.0000
1.000 0.3794 0.01543 0.00618 -0.0253 0.5222 1.0000
1.250 0.4039 0.01552 0.00615 -0.0248 0.5140 1.0000
1.500 0.4284 0.01561 0.00619 -0.0243 0.5049 1.0000
1.750 0.4527 0.01572 0.00621 -0.0237 0.4970 1.0000
2.000 0.4770 0.01584 0.00630 -0.0232 0.4884 1.0000
2.250 0.5011 0.01598 0.00636 -0.0226 0.4811 1.0000
2.500 0.5253 0.01613 0.00649 -0.0220 0.4725 1.0000
2.750 0.5492 0.01629 0.00657 -0.0213 0.4656 1.0000
3.000 0.5732 0.01646 0.00677 -0.0207 0.4572 1.0000
3.250 0.5970 0.01665 0.00687 -0.0200 0.4504 1.0000
3.500 0.6208 0.01684 0.00711 -0.0194 0.4422 1.0000
3.750 0.6444 0.01704 0.00728 -0.0187 0.4352 1.0000
4.000 0.6680 0.01727 0.00752 -0.0180 0.4275 1.0000
4.250 0.6914 0.01749 0.00774 -0.0172 0.4202 1.0000
4.500 0.7147 0.01773 0.00800 -0.0164 0.4130 1.0000
4.750 0.7379 0.01797 0.00827 -0.0157 0.4053 1.0000
5.000 0.7611 0.01823 0.00851 -0.0148 0.3986 1.0000
5.250 0.7839 0.01849 0.00887 -0.0140 0.3904 1.0000
5.500 0.8070 0.01875 0.00909 -0.0132 0.3840 1.0000
5.750 0.8294 0.01905 0.00950 -0.0123 0.3754 1.0000
6.000 0.8522 0.01932 0.00975 -0.0114 0.3687 1.0000
6.250 0.8743 0.01964 0.01020 -0.0105 0.3600 1.0000
6.500 0.8968 0.01992 0.01046 -0.0096 0.3530 1.0000
6.750 0.9184 0.02027 0.01095 -0.0087 0.3439 1.0000
7.000 0.9405 0.02056 0.01122 -0.0077 0.3366 1.0000
7.250 0.9616 0.02093 0.01173 -0.0067 0.3269 1.0000
7.500 0.9828 0.02125 0.01209 -0.0056 0.3186 1.0000
7.750 1.0034 0.02161 0.01255 -0.0045 0.3088 1.0000
8.000 1.0237 0.02199 0.01302 -0.0034 0.2989 1.0000
8.250 1.0436 0.02234 0.01338 -0.0022 0.2892 1.0000
8.500 1.0628 0.02276 0.01393 -0.0010 0.2778 1.0000
8.750 1.0816 0.02321 0.01447 0.0002 0.2661 1.0000
9.000 1.0998 0.02368 0.01500 0.0015 0.2544 1.0000
9.250 1.1171 0.02420 0.01556 0.0029 0.2422 1.0000
9.500 1.1333 0.02479 0.01619 0.0044 0.2295 1.0000
9.750 1.1486 0.02545 0.01693 0.0058 0.2160 1.0000
10.000 1.1625 0.02620 0.01774 0.0074 0.2021 1.0000
10.250 1.1748 0.02705 0.01864 0.0091 0.1883 1.0000
10.500 1.1850 0.02802 0.01966 0.0109 0.1744 1.0000
10.750 1.1929 0.02913 0.02081 0.0128 0.1612 1.0000
11.000 1.1972 0.03038 0.02209 0.0150 0.1488 1.0000
11.250 1.1976 0.03182 0.02356 0.0174 0.1382 1.0000
11.500 1.1959 0.03362 0.02538 0.0193 0.1286 1.0000
11.750 1.1931 0.03580 0.02760 0.0205 0.1197 1.0000
12.000 1.1907 0.03825 0.03014 0.0211 0.1115 1.0000
12.250 1.1845 0.04131 0.03321 0.0211 0.1051 1.0000
12.500 1.1806 0.04442 0.03644 0.0207 0.0984 1.0000
12.750 1.1721 0.04819 0.04021 0.0199 0.0937 1.0000
13.000 1.1677 0.05166 0.04382 0.0192 0.0883 1.0000
13.250 1.1594 0.05566 0.04787 0.0181 0.0843 1.0000
13.500 1.1519 0.05961 0.05187 0.0170 0.0805 1.0000
13.750 1.1456 0.06349 0.05587 0.0160 0.0766 1.0000
14.000 1.1373 0.06764 0.06006 0.0148 0.0736 1.0000
14.250 1.1304 0.07160 0.06405 0.0138 0.0707 1.0000
14.500 1.1253 0.07545 0.06804 0.0127 0.0676 1.0000
14.750 1.1196 0.07950 0.07217 0.0115 0.0649 1.0000
15.000 1.1145 0.08342 0.07608 0.0102 0.0626 1.0000
15.250 1.1108 0.08729 0.08006 0.0091 0.0601 1.0000
15.500 1.1068 0.09134 0.08423 0.0078 0.0577 1.0000
15.750 1.1034 0.09530 0.08825 0.0064 0.0557 1.0000
16.000 1.1019 0.09884 0.09179 0.0053 0.0538 1.0000
16.250 1.0984 0.10295 0.09602 0.0039 0.0520 1.0000
16.500 1.0929 0.10758 0.10081 0.0020 0.0503 1.0000
16.750 1.0884 0.11204 0.10538 0.0002 0.0487 1.0000
17.000 1.0862 0.11606 0.10945 -0.0014 0.0472 1.0000
17.250 1.0897 0.11878 0.11216 -0.0023 0.0458 1.0000
17.500 1.0802 0.12454 0.11810 -0.0050 0.0447 1.0000
17.750 1.0673 0.13123 0.12499 -0.0084 0.0437 1.0000
18.000 1.0520 0.13861 0.13256 -0.0123 0.0429 1.0000
18.250 1.0319 0.14745 0.14158 -0.0172 0.0421 1.0000
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