NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 109.42 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca25112-jf-1000000.txt Download as CSV file: xf-naca25112-jf-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.1781 0.04652 0.04375 -0.0398 1.0000 0.0139
-15.000 -1.1937 0.04219 0.03925 -0.0406 1.0000 0.0140
-14.750 -1.2025 0.03917 0.03609 -0.0398 1.0000 0.0141
-14.500 -1.2061 0.03692 0.03371 -0.0382 1.0000 0.0142
-14.250 -1.2070 0.03504 0.03171 -0.0361 1.0000 0.0143
-14.000 -1.2046 0.03350 0.03006 -0.0338 1.0000 0.0144
-13.750 -1.1998 0.03218 0.02864 -0.0313 1.0000 0.0146
-13.500 -1.1913 0.03093 0.02728 -0.0292 1.0000 0.0148
-13.250 -1.1797 0.02969 0.02592 -0.0275 1.0000 0.0150
-13.000 -1.1667 0.02847 0.02458 -0.0259 1.0000 0.0152
-12.750 -1.1523 0.02730 0.02328 -0.0244 1.0000 0.0155
-12.500 -1.1366 0.02617 0.02201 -0.0230 1.0000 0.0157
-12.250 -1.1194 0.02516 0.02087 -0.0217 1.0000 0.0159
-12.000 -1.1005 0.02428 0.01987 -0.0206 1.0000 0.0160
-11.750 -1.0865 0.02268 0.01809 -0.0189 1.0000 0.0163
-11.500 -1.0703 0.02134 0.01663 -0.0174 1.0000 0.0167
-11.250 -1.0495 0.02058 0.01582 -0.0164 1.0000 0.0170
-11.000 -1.0274 0.01996 0.01515 -0.0155 1.0000 0.0173
-10.750 -1.0048 0.01937 0.01451 -0.0147 1.0000 0.0176
-10.500 -0.9820 0.01877 0.01384 -0.0139 1.0000 0.0180
-10.250 -0.9590 0.01817 0.01317 -0.0131 1.0000 0.0184
-10.000 -0.9357 0.01760 0.01251 -0.0123 1.0000 0.0187
-9.750 -0.9119 0.01708 0.01193 -0.0116 1.0000 0.0191
-9.500 -0.8878 0.01662 0.01140 -0.0109 1.0000 0.0194
-9.250 -0.8676 0.01560 0.01032 -0.0097 1.0000 0.0201
-9.000 -0.8437 0.01518 0.00988 -0.0089 1.0000 0.0206
-8.750 -0.8198 0.01479 0.00947 -0.0081 1.0000 0.0211
-8.500 -0.7963 0.01439 0.00904 -0.0072 1.0000 0.0217
-8.250 -0.7735 0.01401 0.00861 -0.0062 1.0000 0.0222
-8.000 -0.7440 0.01364 0.00819 -0.0065 0.9974 0.0227
-7.750 -0.7105 0.01292 0.00742 -0.0079 0.9902 0.0236
-7.500 -0.6765 0.01247 0.00697 -0.0092 0.9790 0.0245
-7.250 -0.6441 0.01217 0.00666 -0.0101 0.9619 0.0254
-7.000 -0.6168 0.01193 0.00636 -0.0097 0.9368 0.0264
-6.750 -0.5927 0.01176 0.00607 -0.0086 0.9071 0.0270
-6.500 -0.5700 0.01129 0.00550 -0.0073 0.8776 0.0282
-6.250 -0.5451 0.01110 0.00522 -0.0065 0.8492 0.0293
-6.000 -0.5195 0.01095 0.00495 -0.0059 0.8213 0.0304
-5.750 -0.4931 0.01082 0.00471 -0.0054 0.7952 0.0315
-5.500 -0.4678 0.01052 0.00431 -0.0047 0.7704 0.0332
-5.250 -0.4411 0.01037 0.00410 -0.0043 0.7461 0.0348
-5.000 -0.4142 0.01026 0.00388 -0.0040 0.7232 0.0364
-4.750 -0.3878 0.01006 0.00359 -0.0035 0.7019 0.0383
-4.500 -0.3609 0.00989 0.00338 -0.0032 0.6810 0.0406
-4.250 -0.3334 0.00981 0.00322 -0.0030 0.6609 0.0428
-4.000 -0.3066 0.00962 0.00298 -0.0027 0.6424 0.0459
-3.750 -0.2793 0.00952 0.00283 -0.0024 0.6242 0.0488
-3.500 -0.2519 0.00940 0.00265 -0.0022 0.6072 0.0523
-3.250 -0.2245 0.00929 0.00251 -0.0020 0.5917 0.0568
-3.000 -0.1970 0.00919 0.00236 -0.0018 0.5769 0.0612
-2.750 -0.1695 0.00909 0.00224 -0.0016 0.5628 0.0671
-2.500 -0.1420 0.00900 0.00212 -0.0014 0.5497 0.0742
-2.250 -0.1141 0.00892 0.00203 -0.0013 0.5377 0.0811
-2.000 -0.0865 0.00882 0.00193 -0.0012 0.5264 0.0918
-1.750 -0.0589 0.00873 0.00185 -0.0010 0.5157 0.1047
-1.500 -0.0311 0.00863 0.00178 -0.0009 0.5061 0.1203
-1.250 -0.0036 0.00853 0.00172 -0.0008 0.4968 0.1421
-1.000 0.0239 0.00840 0.00166 -0.0007 0.4877 0.1721
-0.750 0.0507 0.00819 0.00160 -0.0005 0.4798 0.2252
-0.500 0.0728 0.00740 0.00147 0.0004 0.4721 0.4316
-0.250 0.0883 0.00628 0.00137 0.0027 0.4652 0.7327
0.000 0.1111 0.00598 0.00140 0.0041 0.4583 0.8315
0.250 0.1368 0.00595 0.00147 0.0049 0.4509 0.8792
0.500 0.1637 0.00597 0.00153 0.0055 0.4444 0.9073
0.750 0.1907 0.00604 0.00159 0.0060 0.4372 0.9261
1.000 0.2179 0.00613 0.00167 0.0064 0.4308 0.9402
1.250 0.2465 0.00623 0.00175 0.0066 0.4239 0.9501
1.500 0.2743 0.00637 0.00183 0.0069 0.4168 0.9590
1.750 0.3051 0.00648 0.00193 0.0065 0.4109 0.9659
2.000 0.3354 0.00662 0.00202 0.0062 0.4038 0.9720
2.250 0.3748 0.00678 0.00215 0.0038 0.3970 0.9752
2.500 0.4184 0.00698 0.00229 0.0006 0.3893 0.9786
2.750 0.4496 0.00712 0.00239 0.0000 0.3827 0.9831
3.000 0.4852 0.00718 0.00243 -0.0017 0.3759 0.9838
3.250 0.5202 0.00730 0.00249 -0.0033 0.3683 0.9847
3.500 0.5551 0.00735 0.00254 -0.0049 0.3620 0.9856
3.750 0.5893 0.00746 0.00260 -0.0063 0.3545 0.9868
4.000 0.6232 0.00754 0.00267 -0.0076 0.3479 0.9882
4.250 0.6563 0.00764 0.00274 -0.0088 0.3404 0.9897
4.500 0.6888 0.00774 0.00282 -0.0099 0.3335 0.9914
4.750 0.7202 0.00785 0.00291 -0.0107 0.3259 0.9932
5.000 0.7533 0.00796 0.00300 -0.0120 0.3183 0.9943
5.250 0.7871 0.00806 0.00308 -0.0134 0.3101 0.9952
5.500 0.8205 0.00818 0.00317 -0.0147 0.3019 0.9961
5.750 0.8534 0.00832 0.00328 -0.0160 0.2922 0.9972
6.000 0.8862 0.00844 0.00339 -0.0172 0.2832 0.9983
6.250 0.9185 0.00861 0.00352 -0.0183 0.2729 0.9993
6.500 0.9491 0.00878 0.00365 -0.0191 0.2622 1.0000
6.750 0.9733 0.00893 0.00379 -0.0186 0.2527 1.0000
7.000 0.9971 0.00913 0.00395 -0.0179 0.2423 1.0000
7.250 1.0205 0.00934 0.00413 -0.0172 0.2312 1.0000
7.500 1.0439 0.00954 0.00431 -0.0165 0.2205 1.0000
7.750 1.0667 0.00979 0.00452 -0.0157 0.2088 1.0000
8.000 1.0890 0.01007 0.00476 -0.0149 0.1964 1.0000
8.250 1.1109 0.01038 0.00502 -0.0139 0.1833 1.0000
8.500 1.1321 0.01072 0.00530 -0.0129 0.1694 1.0000
8.750 1.1528 0.01110 0.00562 -0.0118 0.1551 1.0000
9.000 1.1728 0.01152 0.00597 -0.0106 0.1401 1.0000
9.250 1.1922 0.01197 0.00635 -0.0093 0.1253 1.0000
9.500 1.2109 0.01246 0.00677 -0.0079 0.1109 1.0000
9.750 1.2288 0.01299 0.00723 -0.0064 0.0968 1.0000
10.000 1.2464 0.01354 0.00771 -0.0049 0.0845 1.0000
10.250 1.2640 0.01408 0.00820 -0.0034 0.0741 1.0000
10.500 1.2814 0.01462 0.00870 -0.0019 0.0651 1.0000
10.750 1.2986 0.01518 0.00923 -0.0004 0.0574 1.0000
11.000 1.3156 0.01575 0.00978 0.0011 0.0509 1.0000
11.250 1.3320 0.01638 0.01039 0.0026 0.0453 1.0000
11.500 1.3495 0.01695 0.01096 0.0039 0.0413 1.0000
11.750 1.3661 0.01758 0.01160 0.0052 0.0376 1.0000
12.000 1.3819 0.01824 0.01227 0.0066 0.0345 1.0000
12.250 1.3970 0.01893 0.01299 0.0080 0.0320 1.0000
12.500 1.4104 0.01961 0.01370 0.0097 0.0300 1.0000
12.750 1.4175 0.02053 0.01464 0.0121 0.0281 1.0000
13.000 1.4286 0.02133 0.01551 0.0138 0.0269 1.0000
13.250 1.4385 0.02232 0.01655 0.0152 0.0256 1.0000
13.500 1.4453 0.02365 0.01792 0.0165 0.0244 1.0000
13.750 1.4499 0.02533 0.01967 0.0174 0.0232 1.0000
14.000 1.4593 0.02677 0.02119 0.0178 0.0224 1.0000
14.250 1.4662 0.02858 0.02307 0.0180 0.0216 1.0000
14.500 1.4701 0.03084 0.02539 0.0178 0.0208 1.0000
14.750 1.4698 0.03371 0.02834 0.0173 0.0201 1.0000
15.000 1.4664 0.03707 0.03179 0.0165 0.0195 1.0000
15.250 1.4684 0.03985 0.03467 0.0158 0.0191 1.0000
15.500 1.4674 0.04304 0.03796 0.0149 0.0187 1.0000
15.750 1.4639 0.04652 0.04153 0.0140 0.0183 1.0000
16.000 1.4583 0.05031 0.04541 0.0129 0.0179 1.0000
16.250 1.4498 0.05442 0.04962 0.0118 0.0176 1.0000
16.500 1.4392 0.05885 0.05414 0.0105 0.0173 1.0000
16.750 1.4266 0.06360 0.05898 0.0091 0.0170 1.0000
17.000 1.4120 0.06876 0.06424 0.0075 0.0168 1.0000
17.250 1.3962 0.07423 0.06980 0.0056 0.0165 1.0000
17.500 1.3781 0.08011 0.07579 0.0036 0.0163 1.0000
17.750 1.3672 0.08509 0.08087 0.0018 0.0161 1.0000
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