NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 747A315 (naca747a315-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.52 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca747a315-il-1000000.txt Download as CSV file: xf-naca747a315-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8120 0.08463 0.08270 -0.0335 1.0000 0.0141
-15.250 -0.9050 0.06091 0.05857 -0.0511 1.0000 0.0138
-15.000 -0.9367 0.05315 0.05060 -0.0555 1.0000 0.0137
-14.750 -0.9603 0.04775 0.04500 -0.0572 1.0000 0.0138
-14.500 -0.9746 0.04399 0.04108 -0.0573 1.0000 0.0138
-14.250 -0.9885 0.04060 0.03750 -0.0565 1.0000 0.0139
-14.000 -0.9914 0.03845 0.03521 -0.0554 1.0000 0.0140
-13.750 -0.9940 0.03644 0.03304 -0.0539 1.0000 0.0141
-13.500 -0.9988 0.03422 0.03067 -0.0520 1.0000 0.0141
-13.000 -1.0068 0.02905 0.02487 -0.0482 0.9115 0.0145
-12.750 -1.0071 0.02755 0.02319 -0.0451 0.8901 0.0147
-12.500 -1.0006 0.02663 0.02214 -0.0426 0.8729 0.0149
-12.250 -0.9927 0.02573 0.02112 -0.0401 0.8576 0.0150
-12.000 -0.9822 0.02514 0.02044 -0.0378 0.8430 0.0152
-11.750 -0.9714 0.02447 0.01965 -0.0354 0.8293 0.0154
-11.500 -0.9599 0.02382 0.01887 -0.0331 0.8160 0.0156
-11.250 -0.9453 0.02330 0.01823 -0.0313 0.8034 0.0160
-11.000 -0.9292 0.02244 0.01724 -0.0297 0.7919 0.0162
-10.750 -0.9114 0.02176 0.01643 -0.0284 0.7815 0.0165
-10.500 -0.8926 0.02108 0.01561 -0.0272 0.7713 0.0168
-10.250 -0.8730 0.02038 0.01478 -0.0261 0.7624 0.0171
-10.000 -0.8525 0.01978 0.01404 -0.0251 0.7535 0.0172
-9.750 -0.8308 0.01930 0.01346 -0.0243 0.7457 0.0174
-9.500 -0.8132 0.01772 0.01174 -0.0231 0.7380 0.0180
-9.250 -0.7915 0.01712 0.01108 -0.0223 0.7310 0.0183
-9.000 -0.7690 0.01664 0.01055 -0.0216 0.7238 0.0187
-8.750 -0.7459 0.01624 0.01008 -0.0210 0.7172 0.0191
-8.500 -0.7222 0.01584 0.00964 -0.0204 0.7107 0.0196
-8.250 -0.6984 0.01546 0.00918 -0.0198 0.7040 0.0201
-8.000 -0.6746 0.01501 0.00866 -0.0192 0.6980 0.0205
-7.750 -0.6501 0.01466 0.00825 -0.0188 0.6914 0.0209
-7.500 -0.6271 0.01415 0.00764 -0.0181 0.6850 0.0212
-7.250 -0.6056 0.01344 0.00690 -0.0171 0.6793 0.0220
-7.000 -0.5813 0.01309 0.00652 -0.0166 0.6732 0.0226
-6.750 -0.5565 0.01280 0.00619 -0.0162 0.6673 0.0232
-6.500 -0.5312 0.01251 0.00586 -0.0158 0.6617 0.0240
-6.250 -0.5058 0.01226 0.00556 -0.0155 0.6557 0.0248
-6.000 -0.4805 0.01199 0.00524 -0.0151 0.6502 0.0254
-5.750 -0.4568 0.01152 0.00476 -0.0145 0.6448 0.0267
-5.500 -0.4310 0.01129 0.00450 -0.0142 0.6391 0.0279
-5.250 -0.4050 0.01109 0.00426 -0.0139 0.6339 0.0292
-5.000 -0.3787 0.01088 0.00401 -0.0137 0.6287 0.0303
-4.750 -0.3535 0.01057 0.00369 -0.0133 0.6235 0.0327
-4.500 -0.3270 0.01042 0.00351 -0.0131 0.6184 0.0350
-4.250 -0.3009 0.01017 0.00327 -0.0129 0.6138 0.0382
-4.000 -0.2742 0.01001 0.00309 -0.0127 0.6090 0.0417
-3.750 -0.2480 0.00982 0.00290 -0.0125 0.6041 0.0467
-3.500 -0.2212 0.00965 0.00273 -0.0124 0.6000 0.0529
-3.250 -0.1946 0.00945 0.00258 -0.0122 0.5956 0.0632
-3.000 -0.1686 0.00923 0.00242 -0.0120 0.5911 0.0828
-2.750 -0.1440 0.00891 0.00226 -0.0116 0.5865 0.1306
-2.500 -0.1207 0.00841 0.00209 -0.0111 0.5832 0.2146
-2.000 -0.0805 0.00697 0.00168 -0.0090 0.5760 0.4979
-1.750 -0.0650 0.00605 0.00150 -0.0068 0.5726 0.6974
-1.500 -0.0392 0.00599 0.00158 -0.0064 0.5692 0.7585
-1.250 -0.0107 0.00601 0.00162 -0.0064 0.5664 0.7773
-1.000 0.0179 0.00605 0.00165 -0.0065 0.5635 0.7892
-0.750 0.0467 0.00611 0.00167 -0.0067 0.5605 0.7983
-0.500 0.0748 0.00619 0.00175 -0.0067 0.5577 0.8088
-0.250 0.1024 0.00634 0.00189 -0.0065 0.5546 0.8219
0.000 0.1302 0.00650 0.00206 -0.0063 0.5525 0.8340
0.250 0.1584 0.00660 0.00219 -0.0062 0.5504 0.8410
0.500 0.1871 0.00668 0.00227 -0.0063 0.5481 0.8458
0.750 0.2161 0.00674 0.00230 -0.0066 0.5456 0.8485
1.000 0.2449 0.00675 0.00229 -0.0069 0.5434 0.8508
1.250 0.2735 0.00679 0.00231 -0.0071 0.5412 0.8529
1.500 0.3022 0.00688 0.00238 -0.0074 0.5388 0.8550
1.750 0.3311 0.00693 0.00243 -0.0077 0.5372 0.8570
2.000 0.3603 0.00696 0.00247 -0.0081 0.5357 0.8587
2.250 0.3894 0.00698 0.00250 -0.0085 0.5340 0.8602
2.500 0.4185 0.00701 0.00253 -0.0089 0.5318 0.8617
2.750 0.4476 0.00704 0.00256 -0.0093 0.5291 0.8631
3.000 0.4765 0.00709 0.00259 -0.0097 0.5262 0.8642
3.250 0.5053 0.00718 0.00265 -0.0100 0.5233 0.8653
3.500 0.5342 0.00721 0.00270 -0.0104 0.5212 0.8668
3.750 0.5630 0.00720 0.00273 -0.0108 0.5187 0.8683
4.000 0.5917 0.00720 0.00275 -0.0111 0.5146 0.8696
4.250 0.6202 0.00724 0.00279 -0.0114 0.5102 0.8708
4.500 0.6484 0.00731 0.00286 -0.0116 0.5051 0.8722
4.750 0.6771 0.00729 0.00288 -0.0120 0.4987 0.8736
5.000 0.7049 0.00737 0.00294 -0.0121 0.4915 0.8751
5.250 0.7335 0.00738 0.00300 -0.0125 0.4855 0.8766
5.500 0.7616 0.00744 0.00306 -0.0128 0.4788 0.8783
5.750 0.7896 0.00752 0.00315 -0.0130 0.4720 0.8800
6.000 0.8174 0.00759 0.00323 -0.0132 0.4613 0.8814
6.250 0.8448 0.00768 0.00331 -0.0134 0.4464 0.8828
6.500 0.8710 0.00781 0.00340 -0.0134 0.4239 0.8847
6.750 0.8890 0.00849 0.00377 -0.0122 0.3532 0.8869
7.000 0.9014 0.00951 0.00442 -0.0102 0.2778 0.8896
7.250 0.9137 0.01044 0.00504 -0.0082 0.2155 0.8926
7.500 0.9260 0.01126 0.00562 -0.0061 0.1671 0.8957
7.750 0.9364 0.01206 0.00621 -0.0038 0.1258 0.8987
8.000 0.9450 0.01275 0.00677 -0.0011 0.0956 0.9029
8.250 0.9481 0.01337 0.00731 0.0028 0.0752 0.9078
8.500 0.9495 0.01413 0.00799 0.0066 0.0574 0.9133
8.750 0.9516 0.01495 0.00877 0.0100 0.0427 0.9195
9.000 0.9578 0.01573 0.00955 0.0126 0.0356 0.9260
9.250 0.9663 0.01648 0.01032 0.0147 0.0315 0.9329
9.500 0.9748 0.01727 0.01115 0.0167 0.0289 0.9417
9.750 0.9862 0.01809 0.01204 0.0181 0.0266 0.9527
10.000 1.0068 0.01903 0.01303 0.0173 0.0244 0.9655
10.250 1.0351 0.02022 0.01427 0.0145 0.0223 0.9768
10.500 1.0592 0.02133 0.01540 0.0127 0.0205 1.0000
10.750 1.0690 0.02251 0.01660 0.0136 0.0195 1.0000
11.000 1.0762 0.02392 0.01806 0.0147 0.0186 1.0000
11.250 1.0883 0.02499 0.01916 0.0153 0.0180 1.0000
11.500 1.0989 0.02619 0.02039 0.0160 0.0174 1.0000
11.750 1.1091 0.02744 0.02167 0.0168 0.0166 1.0000
12.000 1.1174 0.02885 0.02310 0.0175 0.0162 1.0000
12.250 1.1235 0.03045 0.02474 0.0183 0.0158 1.0000
12.500 1.1235 0.03258 0.02693 0.0193 0.0153 1.0000
12.750 1.1332 0.03395 0.02836 0.0198 0.0151 1.0000
13.000 1.1432 0.03534 0.02979 0.0203 0.0148 1.0000
13.250 1.1504 0.03701 0.03151 0.0207 0.0146 1.0000
13.500 1.1573 0.03873 0.03329 0.0212 0.0143 1.0000
13.750 1.1677 0.04017 0.03476 0.0214 0.0138 1.0000
14.000 1.1738 0.04204 0.03668 0.0217 0.0136 1.0000
14.250 1.1807 0.04386 0.03855 0.0219 0.0134 1.0000
14.500 1.1864 0.04583 0.04057 0.0221 0.0132 1.0000
14.750 1.1904 0.04799 0.04277 0.0223 0.0130 1.0000
15.000 1.1898 0.05066 0.04550 0.0224 0.0126 1.0000
15.250 1.1878 0.05349 0.04839 0.0226 0.0124 1.0000
15.500 1.1890 0.05602 0.05099 0.0227 0.0123 1.0000
15.750 1.1954 0.05814 0.05318 0.0225 0.0122 1.0000
16.000 1.2013 0.06032 0.05543 0.0223 0.0121 1.0000
16.250 1.2062 0.06267 0.05785 0.0220 0.0120 1.0000
16.500 1.2098 0.06513 0.06038 0.0218 0.0119 1.0000
16.750 1.2130 0.06771 0.06302 0.0214 0.0118 1.0000
17.000 1.2167 0.07027 0.06566 0.0209 0.0117 1.0000
17.250 1.2190 0.07309 0.06855 0.0204 0.0115 1.0000
17.500 1.2216 0.07586 0.07140 0.0198 0.0114 1.0000
17.750 1.2228 0.07886 0.07447 0.0191 0.0113 1.0000
18.000 1.2236 0.08193 0.07762 0.0183 0.0113 1.0000
18.250 1.2247 0.08514 0.08091 0.0173 0.0110 1.0000
18.500 1.2262 0.08827 0.08412 0.0163 0.0110 1.0000
18.750 1.2257 0.09176 0.08768 0.0151 0.0109 1.0000
19.000 1.2246 0.09534 0.09135 0.0138 0.0108 1.0000
19.250 1.2231 0.09908 0.09518 0.0124 0.0107 1.0000
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