NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A315 (naca747a315-il) Reynolds number: 500,000 Max Cl/Cd: 85.08 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a315-il-500000-n5.txt Download as CSV file: xf-naca747a315-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A315
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9326 0.05816 0.05484 -0.0518 1.0000 0.0134
-15.000 -0.9554 0.05204 0.04852 -0.0548 1.0000 0.0135
-14.750 -0.9665 0.04812 0.04446 -0.0559 1.0000 0.0136
-14.500 -0.9784 0.04450 0.04067 -0.0561 1.0000 0.0137
-14.250 -0.9842 0.04176 0.03781 -0.0556 1.0000 0.0138
-14.000 -0.9843 0.03972 0.03568 -0.0549 1.0000 0.0139
-13.500 -0.9726 0.03583 0.03149 -0.0548 0.9266 0.0141
-13.250 -0.9709 0.03444 0.02991 -0.0528 0.8969 0.0143
-13.000 -0.9705 0.03299 0.02825 -0.0503 0.8753 0.0144
-12.750 -0.9665 0.03181 0.02689 -0.0481 0.8576 0.0145
-12.500 -0.9616 0.03060 0.02551 -0.0457 0.8414 0.0147
-12.250 -0.9551 0.02944 0.02416 -0.0435 0.8271 0.0149
-12.000 -0.9473 0.02831 0.02284 -0.0413 0.8135 0.0152
-11.750 -0.9379 0.02727 0.02161 -0.0391 0.8008 0.0154
-11.500 -0.9276 0.02619 0.02033 -0.0370 0.7891 0.0156
-11.250 -0.9153 0.02521 0.01916 -0.0350 0.7783 0.0159
-11.000 -0.9016 0.02438 0.01814 -0.0332 0.7687 0.0161
-10.750 -0.8860 0.02367 0.01725 -0.0315 0.7592 0.0164
-10.500 -0.8700 0.02273 0.01620 -0.0301 0.7509 0.0167
-10.250 -0.8519 0.02202 0.01540 -0.0289 0.7422 0.0170
-10.000 -0.8325 0.02140 0.01468 -0.0278 0.7345 0.0172
-9.750 -0.8124 0.02078 0.01397 -0.0269 0.7266 0.0175
-9.500 -0.7916 0.02021 0.01329 -0.0260 0.7195 0.0179
-9.250 -0.7703 0.01962 0.01261 -0.0251 0.7126 0.0182
-9.000 -0.7487 0.01904 0.01192 -0.0243 0.7062 0.0186
-8.750 -0.7264 0.01851 0.01129 -0.0236 0.7003 0.0190
-8.500 -0.7038 0.01798 0.01067 -0.0229 0.6939 0.0195
-8.250 -0.6809 0.01752 0.01009 -0.0222 0.6880 0.0199
-8.000 -0.6591 0.01689 0.00943 -0.0214 0.6823 0.0203
-7.750 -0.6361 0.01644 0.00893 -0.0208 0.6762 0.0207
-7.250 -0.5891 0.01562 0.00800 -0.0196 0.6650 0.0218
-7.000 -0.5653 0.01523 0.00755 -0.0190 0.6591 0.0224
-6.500 -0.5167 0.01454 0.00672 -0.0180 0.6483 0.0237
-6.250 -0.4930 0.01413 0.00629 -0.0174 0.6426 0.0246
-5.750 -0.4433 0.01356 0.00564 -0.0166 0.6319 0.0268
-5.500 -0.4181 0.01329 0.00531 -0.0162 0.6265 0.0280
-5.250 -0.3934 0.01300 0.00498 -0.0158 0.6216 0.0293
-5.000 -0.3680 0.01274 0.00471 -0.0154 0.6172 0.0311
-4.750 -0.3422 0.01252 0.00445 -0.0151 0.6124 0.0330
-4.500 -0.3167 0.01229 0.00420 -0.0148 0.6078 0.0354
-4.250 -0.2909 0.01209 0.00398 -0.0146 0.6037 0.0385
-4.000 -0.2647 0.01189 0.00377 -0.0143 0.5996 0.0422
-3.750 -0.2385 0.01170 0.00359 -0.0141 0.5953 0.0470
-3.500 -0.2125 0.01151 0.00340 -0.0139 0.5913 0.0530
-3.000 -0.1604 0.01112 0.00307 -0.0135 0.5841 0.0754
-2.750 -0.1350 0.01085 0.00290 -0.0132 0.5803 0.1025
-2.500 -0.1107 0.01050 0.00274 -0.0128 0.5767 0.1545
-2.250 -0.0878 0.01005 0.00256 -0.0122 0.5734 0.2322
-2.000 -0.0663 0.00950 0.00238 -0.0114 0.5705 0.3364
-1.750 -0.0465 0.00881 0.00218 -0.0103 0.5674 0.4661
-1.500 -0.0291 0.00803 0.00197 -0.0086 0.5642 0.6119
-1.250 -0.0083 0.00770 0.00210 -0.0070 0.5610 0.7320
-1.000 0.0184 0.00776 0.00219 -0.0066 0.5580 0.7702
-0.750 0.0447 0.00790 0.00236 -0.0061 0.5554 0.8002
-0.500 0.0712 0.00808 0.00255 -0.0055 0.5530 0.8208
-0.250 0.0988 0.00822 0.00271 -0.0052 0.5505 0.8303
0.000 0.1271 0.00828 0.00273 -0.0053 0.5480 0.8358
0.250 0.1556 0.00831 0.00274 -0.0055 0.5456 0.8385
0.500 0.1841 0.00836 0.00277 -0.0056 0.5434 0.8410
0.750 0.2125 0.00842 0.00280 -0.0058 0.5413 0.8436
1.000 0.2410 0.00848 0.00282 -0.0060 0.5393 0.8458
1.250 0.2698 0.00851 0.00283 -0.0063 0.5375 0.8477
1.500 0.2986 0.00854 0.00286 -0.0066 0.5356 0.8494
1.750 0.3274 0.00857 0.00288 -0.0070 0.5335 0.8512
2.000 0.3562 0.00860 0.00291 -0.0073 0.5313 0.8528
2.250 0.3850 0.00865 0.00294 -0.0077 0.5293 0.8541
2.500 0.4136 0.00869 0.00298 -0.0080 0.5276 0.8553
2.750 0.4421 0.00874 0.00304 -0.0083 0.5259 0.8566
3.000 0.4705 0.00881 0.00312 -0.0085 0.5242 0.8580
3.250 0.4989 0.00889 0.00319 -0.0088 0.5220 0.8593
3.500 0.5275 0.00892 0.00327 -0.0091 0.5191 0.8607
3.750 0.5559 0.00896 0.00335 -0.0094 0.5157 0.8621
4.000 0.5842 0.00902 0.00343 -0.0097 0.5129 0.8636
4.250 0.6125 0.00909 0.00351 -0.0099 0.5102 0.8651
4.500 0.6404 0.00919 0.00359 -0.0102 0.5062 0.8667
4.750 0.6685 0.00921 0.00368 -0.0104 0.5002 0.8686
5.000 0.6959 0.00927 0.00374 -0.0105 0.4926 0.8703
5.250 0.7232 0.00932 0.00382 -0.0106 0.4833 0.8718
5.500 0.7497 0.00939 0.00390 -0.0106 0.4712 0.8732
5.750 0.7761 0.00948 0.00400 -0.0105 0.4594 0.8748
6.000 0.8028 0.00957 0.00414 -0.0105 0.4468 0.8764
6.250 0.8278 0.00973 0.00427 -0.0103 0.4225 0.8782
6.500 0.8440 0.01037 0.00459 -0.0088 0.3546 0.8808
6.750 0.8553 0.01135 0.00525 -0.0067 0.2886 0.8839
7.000 0.8661 0.01229 0.00592 -0.0046 0.2319 0.8870
7.250 0.8750 0.01317 0.00658 -0.0021 0.1856 0.8902
7.500 0.8819 0.01399 0.00724 0.0008 0.1464 0.8942
7.750 0.8838 0.01475 0.00786 0.0046 0.1162 0.8992
8.000 0.8865 0.01558 0.00861 0.0079 0.0950 0.9043
8.250 0.8903 0.01644 0.00942 0.0109 0.0772 0.9094
8.500 0.8944 0.01742 0.01034 0.0135 0.0601 0.9156
9.000 0.9078 0.01938 0.01226 0.0175 0.0386 0.9292
9.250 0.9178 0.02033 0.01325 0.0188 0.0337 0.9373
9.500 0.9314 0.02129 0.01425 0.0195 0.0304 0.9474
9.750 0.9505 0.02241 0.01542 0.0187 0.0276 0.9580
10.000 0.9751 0.02356 0.01663 0.0167 0.0254 0.9689
10.250 0.9972 0.02484 0.01795 0.0149 0.0231 1.0000
10.500 1.0070 0.02608 0.01920 0.0157 0.0220 1.0000
10.750 1.0182 0.02724 0.02041 0.0164 0.0208 1.0000
11.000 1.0283 0.02849 0.02170 0.0171 0.0197 1.0000
11.250 1.0370 0.02987 0.02310 0.0178 0.0186 1.0000
11.500 1.0455 0.03130 0.02456 0.0185 0.0180 1.0000
11.750 1.0555 0.03262 0.02594 0.0190 0.0174 1.0000
12.000 1.0644 0.03406 0.02742 0.0196 0.0166 1.0000
12.250 1.0728 0.03555 0.02895 0.0201 0.0159 1.0000
12.500 1.0806 0.03714 0.03058 0.0206 0.0155 1.0000
12.750 1.0865 0.03892 0.03239 0.0211 0.0149 1.0000
13.000 1.0934 0.04067 0.03420 0.0214 0.0147 1.0000
13.250 1.1012 0.04239 0.03598 0.0217 0.0144 1.0000
13.500 1.1084 0.04419 0.03784 0.0220 0.0140 1.0000
13.750 1.1150 0.04607 0.03979 0.0222 0.0138 1.0000
14.000 1.1219 0.04797 0.04175 0.0223 0.0134 1.0000
14.250 1.1280 0.04999 0.04382 0.0223 0.0131 1.0000
14.500 1.1340 0.05205 0.04594 0.0223 0.0129 1.0000
14.750 1.1397 0.05418 0.04814 0.0223 0.0128 1.0000
15.000 1.1448 0.05641 0.05042 0.0221 0.0125 1.0000
15.250 1.1485 0.05884 0.05291 0.0219 0.0124 1.0000
15.500 1.1517 0.06136 0.05549 0.0217 0.0122 1.0000
15.750 1.1529 0.06415 0.05833 0.0213 0.0120 1.0000
16.000 1.1572 0.06662 0.06089 0.0210 0.0118 1.0000
16.250 1.1604 0.06929 0.06364 0.0205 0.0117 1.0000
16.500 1.1638 0.07198 0.06641 0.0200 0.0116 1.0000
16.750 1.1660 0.07485 0.06937 0.0193 0.0116 1.0000
17.000 1.1685 0.07772 0.07233 0.0186 0.0114 1.0000
17.250 1.1699 0.08079 0.07549 0.0178 0.0113 1.0000
17.500 1.1712 0.08395 0.07875 0.0169 0.0111 1.0000
17.750 1.1729 0.08713 0.08202 0.0159 0.0109 1.0000
18.000 1.1735 0.09047 0.08545 0.0148 0.0108 1.0000
18.250 1.1743 0.09385 0.08892 0.0135 0.0108 1.0000
18.500 1.1733 0.09758 0.09274 0.0121 0.0106 1.0000
18.750 1.1725 0.10136 0.09661 0.0106 0.0105 1.0000
19.000 1.1710 0.10526 0.10061 0.0089 0.0104 1.0000
19.250 1.1695 0.10922 0.10467 0.0072 0.0103 1.0000
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Polar data table (+)
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