NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 98.11 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca25112-jf-1000000-n5.txt Download as CSV file: xf-naca25112-jf-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.2923 0.05073 0.04779 -0.0392 1.0000 0.0105
-16.500 -1.3204 0.04425 0.04108 -0.0420 1.0000 0.0105
-16.250 -1.3344 0.04041 0.03707 -0.0419 1.0000 0.0105
-16.000 -1.3418 0.03763 0.03413 -0.0407 1.0000 0.0106
-15.750 -1.3450 0.03543 0.03179 -0.0389 1.0000 0.0106
-15.500 -1.3446 0.03363 0.02985 -0.0368 1.0000 0.0107
-15.250 -1.3467 0.03176 0.02785 -0.0341 1.0000 0.0108
-15.000 -1.3440 0.03026 0.02624 -0.0314 1.0000 0.0110
-14.750 -1.3364 0.02898 0.02487 -0.0291 1.0000 0.0111
-14.500 -1.3241 0.02783 0.02363 -0.0274 1.0000 0.0113
-14.250 -1.3097 0.02678 0.02250 -0.0259 1.0000 0.0115
-14.000 -1.2938 0.02582 0.02145 -0.0245 1.0000 0.0116
-13.750 -1.2768 0.02490 0.02045 -0.0232 1.0000 0.0118
-13.500 -1.2589 0.02404 0.01950 -0.0220 1.0000 0.0120
-13.250 -1.2401 0.02322 0.01859 -0.0208 1.0000 0.0121
-13.000 -1.2206 0.02243 0.01772 -0.0197 1.0000 0.0123
-12.750 -1.2004 0.02168 0.01689 -0.0187 1.0000 0.0125
-12.500 -1.1796 0.02097 0.01610 -0.0177 1.0000 0.0127
-12.250 -1.1582 0.02030 0.01534 -0.0168 1.0000 0.0129
-12.000 -1.1363 0.01966 0.01462 -0.0159 1.0000 0.0130
-11.750 -1.1138 0.01907 0.01396 -0.0151 1.0000 0.0132
-11.500 -1.0921 0.01837 0.01319 -0.0142 1.0000 0.0134
-11.250 -1.0696 0.01773 0.01250 -0.0134 1.0000 0.0138
-11.000 -1.0463 0.01719 0.01192 -0.0126 1.0000 0.0140
-10.750 -1.0225 0.01669 0.01138 -0.0119 1.0000 0.0143
-10.500 -0.9985 0.01622 0.01087 -0.0113 1.0000 0.0146
-10.250 -0.9743 0.01578 0.01039 -0.0106 1.0000 0.0150
-10.000 -0.9499 0.01537 0.00993 -0.0100 1.0000 0.0154
-9.750 -0.9254 0.01497 0.00948 -0.0093 1.0000 0.0157
-9.500 -0.8980 0.01457 0.00904 -0.0093 0.9947 0.0160
-9.250 -0.8669 0.01406 0.00849 -0.0101 0.9787 0.0165
-9.000 -0.8359 0.01364 0.00803 -0.0107 0.9562 0.0170
-8.750 -0.8105 0.01333 0.00765 -0.0101 0.9252 0.0175
-8.500 -0.7871 0.01308 0.00729 -0.0090 0.8926 0.0179
-8.250 -0.7630 0.01286 0.00693 -0.0080 0.8613 0.0184
-8.000 -0.7381 0.01264 0.00658 -0.0073 0.8328 0.0189
-7.500 -0.6870 0.01217 0.00590 -0.0061 0.7794 0.0201
-7.250 -0.6610 0.01196 0.00560 -0.0057 0.7556 0.0209
-7.000 -0.6346 0.01177 0.00531 -0.0053 0.7327 0.0216
-6.750 -0.6081 0.01159 0.00504 -0.0049 0.7105 0.0223
-6.500 -0.5813 0.01142 0.00477 -0.0045 0.6900 0.0229
-6.250 -0.5548 0.01120 0.00449 -0.0042 0.6703 0.0240
-6.000 -0.5280 0.01103 0.00425 -0.0039 0.6511 0.0250
-5.750 -0.5009 0.01088 0.00403 -0.0036 0.6336 0.0262
-5.500 -0.4737 0.01075 0.00382 -0.0034 0.6168 0.0272
-5.250 -0.4468 0.01057 0.00360 -0.0031 0.6002 0.0286
-5.000 -0.4195 0.01043 0.00341 -0.0028 0.5850 0.0301
-4.750 -0.3920 0.01031 0.00323 -0.0026 0.5711 0.0314
-4.500 -0.3647 0.01016 0.00305 -0.0024 0.5575 0.0333
-4.250 -0.3373 0.01004 0.00289 -0.0022 0.5448 0.0354
-4.000 -0.3096 0.00995 0.00274 -0.0021 0.5330 0.0371
-3.750 -0.2821 0.00981 0.00259 -0.0019 0.5217 0.0398
-3.500 -0.2544 0.00972 0.00246 -0.0017 0.5113 0.0426
-3.250 -0.2268 0.00961 0.00234 -0.0016 0.5013 0.0458
-3.000 -0.1989 0.00951 0.00222 -0.0014 0.4926 0.0492
-2.500 -0.1433 0.00934 0.00202 -0.0012 0.4753 0.0579
-2.250 -0.1154 0.00926 0.00193 -0.0011 0.4673 0.0631
-2.000 -0.0874 0.00918 0.00185 -0.0010 0.4599 0.0688
-1.750 -0.0596 0.00910 0.00178 -0.0009 0.4522 0.0767
-1.500 -0.0315 0.00903 0.00171 -0.0009 0.4459 0.0845
-1.250 -0.0035 0.00896 0.00166 -0.0008 0.4387 0.0942
-1.000 0.0244 0.00890 0.00161 -0.0007 0.4318 0.1062
-0.750 0.0524 0.00882 0.00157 -0.0007 0.4257 0.1212
-0.500 0.0803 0.00876 0.00153 -0.0006 0.4188 0.1390
-0.250 0.1081 0.00866 0.00150 -0.0005 0.4129 0.1644
0.000 0.1357 0.00854 0.00147 -0.0004 0.4065 0.2001
0.250 0.1626 0.00836 0.00145 -0.0003 0.4003 0.2596
0.500 0.1801 0.00710 0.00131 0.0013 0.3953 0.6115
0.750 0.2029 0.00668 0.00130 0.0024 0.3891 0.7374
1.000 0.2271 0.00647 0.00134 0.0034 0.3834 0.8150
1.500 0.2801 0.00641 0.00146 0.0045 0.3711 0.8903
1.750 0.3076 0.00646 0.00153 0.0048 0.3657 0.9113
2.000 0.3353 0.00652 0.00160 0.0050 0.3594 0.9271
2.250 0.3627 0.00663 0.00169 0.0053 0.3530 0.9413
2.500 0.3910 0.00672 0.00179 0.0055 0.3475 0.9541
2.750 0.4210 0.00685 0.00189 0.0052 0.3406 0.9617
3.000 0.4502 0.00695 0.00196 0.0050 0.3348 0.9655
3.250 0.4780 0.00704 0.00202 0.0050 0.3285 0.9696
3.500 0.5085 0.00716 0.00210 0.0045 0.3214 0.9717
3.750 0.5399 0.00725 0.00218 0.0037 0.3154 0.9734
4.000 0.5710 0.00738 0.00227 0.0030 0.3079 0.9753
4.250 0.6019 0.00750 0.00236 0.0023 0.3016 0.9774
4.500 0.6319 0.00763 0.00246 0.0018 0.2939 0.9797
4.750 0.6600 0.00776 0.00257 0.0017 0.2872 0.9825
5.000 0.6916 0.00790 0.00268 0.0009 0.2788 0.9837
5.250 0.7240 0.00805 0.00280 -0.0002 0.2710 0.9845
5.500 0.7561 0.00822 0.00294 -0.0013 0.2617 0.9854
5.750 0.7878 0.00838 0.00307 -0.0023 0.2526 0.9863
6.000 0.8190 0.00858 0.00323 -0.0032 0.2419 0.9875
6.500 0.8797 0.00903 0.00358 -0.0047 0.2177 0.9902
6.750 0.9092 0.00928 0.00378 -0.0053 0.2050 0.9917
7.000 0.9377 0.00956 0.00401 -0.0057 0.1915 0.9933
7.250 0.9674 0.00986 0.00425 -0.0064 0.1773 0.9943
7.500 0.9976 0.01020 0.00452 -0.0072 0.1625 0.9951
7.750 1.0271 0.01057 0.00482 -0.0080 0.1475 0.9961
8.000 1.0560 0.01099 0.00515 -0.0087 0.1316 0.9972
8.250 1.0847 0.01141 0.00551 -0.0094 0.1168 0.9983
8.500 1.1130 0.01187 0.00589 -0.0100 0.1024 0.9993
8.750 1.1391 0.01233 0.00629 -0.0101 0.0894 1.0000
9.000 1.1583 0.01277 0.00668 -0.0088 0.0787 1.0000
9.250 1.1770 0.01322 0.00709 -0.0074 0.0694 1.0000
9.500 1.1956 0.01368 0.00751 -0.0059 0.0615 1.0000
9.750 1.2140 0.01413 0.00793 -0.0045 0.0544 1.0000
10.000 1.2328 0.01456 0.00835 -0.0032 0.0489 1.0000
10.250 1.2511 0.01502 0.00880 -0.0018 0.0443 1.0000
10.500 1.2693 0.01548 0.00925 -0.0004 0.0401 1.0000
10.750 1.2876 0.01594 0.00972 0.0010 0.0367 1.0000
11.000 1.3051 0.01647 0.01024 0.0023 0.0332 1.0000
11.250 1.3236 0.01695 0.01074 0.0035 0.0309 1.0000
11.500 1.3411 0.01750 0.01130 0.0048 0.0286 1.0000
11.750 1.3588 0.01804 0.01187 0.0060 0.0267 1.0000
12.000 1.3755 0.01864 0.01249 0.0072 0.0249 1.0000
12.250 1.3906 0.01930 0.01317 0.0086 0.0232 1.0000
12.500 1.4041 0.01991 0.01382 0.0103 0.0221 1.0000
12.750 1.4149 0.02064 0.01459 0.0123 0.0210 1.0000
13.000 1.4247 0.02154 0.01553 0.0140 0.0199 1.0000
13.250 1.4352 0.02250 0.01655 0.0153 0.0192 1.0000
13.500 1.4455 0.02360 0.01770 0.0163 0.0184 1.0000
13.750 1.4542 0.02492 0.01908 0.0171 0.0176 1.0000
14.000 1.4614 0.02652 0.02073 0.0176 0.0168 1.0000
14.250 1.4674 0.02838 0.02266 0.0178 0.0161 1.0000
14.500 1.4745 0.03029 0.02465 0.0177 0.0157 1.0000
14.750 1.4797 0.03249 0.02692 0.0174 0.0152 1.0000
15.000 1.4830 0.03500 0.02952 0.0169 0.0147 1.0000
15.250 1.4842 0.03782 0.03242 0.0162 0.0143 1.0000
15.500 1.4832 0.04096 0.03564 0.0154 0.0139 1.0000
15.750 1.4797 0.04442 0.03919 0.0145 0.0136 1.0000
16.000 1.4739 0.04820 0.04305 0.0134 0.0133 1.0000
16.250 1.4689 0.05187 0.04683 0.0124 0.0131 1.0000
16.500 1.4619 0.05580 0.05085 0.0113 0.0129 1.0000
16.750 1.4537 0.05990 0.05505 0.0102 0.0128 1.0000
17.000 1.4442 0.06426 0.05951 0.0089 0.0126 1.0000
17.250 1.4343 0.06880 0.06414 0.0074 0.0124 1.0000
17.500 1.4239 0.07348 0.06892 0.0059 0.0122 1.0000
17.750 1.4130 0.07829 0.07382 0.0043 0.0120 1.0000
18.000 1.4019 0.08323 0.07885 0.0025 0.0119 1.0000
18.250 1.3904 0.08829 0.08400 0.0007 0.0117 1.0000
18.500 1.3784 0.09347 0.08927 -0.0012 0.0115 1.0000
18.750 1.3663 0.09877 0.09465 -0.0033 0.0114 1.0000
19.000 1.3541 0.10415 0.10012 -0.0054 0.0112 1.0000
19.250 1.3416 0.10959 0.10564 -0.0076 0.0110 1.0000
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