NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.88 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a415-il-1000000-n5.txt Download as CSV file: xf-naca747a415-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A415
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
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0405 0.06637 0.06372 -0.0561 1.0000 0.0102
-17.250 -1.0794 0.05542 0.05253 -0.0640 1.0000 0.0102
-17.000 -1.0983 0.04936 0.04631 -0.0676 1.0000 0.0102
-16.750 -1.1166 0.04436 0.04113 -0.0695 1.0000 0.0102
-16.500 -1.1260 0.04091 0.03755 -0.0700 1.0000 0.0102
-16.250 -1.1298 0.03828 0.03479 -0.0698 1.0000 0.0103
-16.000 -1.1295 0.03617 0.03257 -0.0693 1.0000 0.0104
-15.750 -1.1295 0.03416 0.03045 -0.0684 1.0000 0.0104
-15.500 -1.1285 0.03234 0.02852 -0.0672 1.0000 0.0105
-15.000 -1.1086 0.02876 0.02467 -0.0679 0.9365 0.0108
-14.750 -1.1023 0.02772 0.02344 -0.0660 0.9027 0.0109
-14.500 -1.0962 0.02677 0.02235 -0.0639 0.8789 0.0110
-14.250 -1.0879 0.02593 0.02136 -0.0619 0.8587 0.0111
-14.000 -1.0775 0.02519 0.02051 -0.0600 0.8416 0.0113
-13.750 -1.0672 0.02442 0.01962 -0.0581 0.8255 0.0115
-13.500 -1.0549 0.02377 0.01886 -0.0564 0.8103 0.0116
-13.250 -1.0442 0.02299 0.01795 -0.0544 0.7962 0.0118
-13.000 -1.0291 0.02251 0.01737 -0.0528 0.7830 0.0120
-12.750 -1.0174 0.02178 0.01651 -0.0507 0.7709 0.0122
-12.500 -1.0031 0.02122 0.01585 -0.0489 0.7605 0.0124
-12.250 -0.9888 0.02067 0.01518 -0.0470 0.7509 0.0125
-12.000 -0.9734 0.02011 0.01451 -0.0453 0.7420 0.0127
-11.750 -0.9550 0.01959 0.01389 -0.0440 0.7341 0.0128
-11.500 -0.9357 0.01907 0.01327 -0.0429 0.7263 0.0130
-11.250 -0.9174 0.01844 0.01253 -0.0417 0.7187 0.0132
-11.000 -0.8978 0.01786 0.01188 -0.0406 0.7120 0.0134
-10.750 -0.8767 0.01740 0.01135 -0.0397 0.7052 0.0137
-10.500 -0.8549 0.01696 0.01085 -0.0390 0.6992 0.0139
-10.250 -0.8321 0.01658 0.01043 -0.0383 0.6932 0.0142
-10.000 -0.8091 0.01622 0.01000 -0.0377 0.6871 0.0145
-9.750 -0.7858 0.01586 0.00958 -0.0371 0.6817 0.0148
-9.500 -0.7623 0.01548 0.00913 -0.0365 0.6758 0.0151
-9.250 -0.7387 0.01512 0.00870 -0.0360 0.6698 0.0154
-9.000 -0.7148 0.01475 0.00826 -0.0354 0.6645 0.0156
-8.750 -0.6905 0.01442 0.00786 -0.0350 0.6586 0.0158
-8.500 -0.6667 0.01403 0.00741 -0.0344 0.6526 0.0161
-8.250 -0.6427 0.01362 0.00696 -0.0339 0.6475 0.0165
-8.000 -0.6179 0.01331 0.00661 -0.0335 0.6418 0.0169
-7.750 -0.5928 0.01304 0.00630 -0.0331 0.6361 0.0173
-7.500 -0.5673 0.01278 0.00601 -0.0328 0.6312 0.0177
-7.250 -0.5418 0.01252 0.00570 -0.0325 0.6256 0.0182
-7.000 -0.5162 0.01227 0.00539 -0.0322 0.6199 0.0186
-6.750 -0.4904 0.01203 0.00511 -0.0320 0.6152 0.0189
-6.500 -0.4644 0.01180 0.00484 -0.0317 0.6097 0.0193
-6.250 -0.4389 0.01152 0.00452 -0.0314 0.6045 0.0199
-6.000 -0.4127 0.01130 0.00429 -0.0312 0.6000 0.0207
-5.750 -0.3862 0.01110 0.00407 -0.0310 0.5957 0.0214
-5.500 -0.3596 0.01092 0.00386 -0.0309 0.5909 0.0222
-5.250 -0.3329 0.01076 0.00365 -0.0308 0.5863 0.0228
-5.000 -0.3064 0.01055 0.00343 -0.0306 0.5825 0.0239
-4.750 -0.2796 0.01038 0.00326 -0.0305 0.5783 0.0251
-4.500 -0.2526 0.01023 0.00309 -0.0304 0.5740 0.0265
-4.250 -0.2256 0.01010 0.00292 -0.0303 0.5698 0.0279
-4.000 -0.1986 0.00994 0.00278 -0.0303 0.5663 0.0303
-3.750 -0.1712 0.00981 0.00264 -0.0303 0.5627 0.0327
-3.500 -0.1440 0.00967 0.00251 -0.0302 0.5588 0.0362
-3.250 -0.1167 0.00956 0.00239 -0.0302 0.5551 0.0400
-3.000 -0.0893 0.00945 0.00228 -0.0302 0.5518 0.0449
-2.750 -0.0618 0.00932 0.00218 -0.0303 0.5489 0.0516
-2.500 -0.0344 0.00919 0.00209 -0.0303 0.5458 0.0602
-2.250 -0.0070 0.00906 0.00199 -0.0303 0.5427 0.0728
-2.000 0.0199 0.00890 0.00191 -0.0303 0.5396 0.0950
-1.500 0.0719 0.00835 0.00172 -0.0300 0.5342 0.2061
-1.250 0.0967 0.00794 0.00162 -0.0298 0.5316 0.2993
-1.000 0.1213 0.00751 0.00152 -0.0295 0.5291 0.4018
-0.750 0.1457 0.00707 0.00142 -0.0292 0.5267 0.5066
-0.500 0.1662 0.00632 0.00131 -0.0281 0.5245 0.6910
-0.250 0.1921 0.00623 0.00142 -0.0277 0.5222 0.7646
0.000 0.2202 0.00629 0.00150 -0.0277 0.5200 0.7887
0.250 0.2485 0.00636 0.00158 -0.0277 0.5185 0.8047
0.500 0.2769 0.00639 0.00165 -0.0278 0.5168 0.8123
0.750 0.3059 0.00644 0.00169 -0.0281 0.5151 0.8170
1.000 0.3350 0.00649 0.00171 -0.0284 0.5133 0.8197
1.250 0.3641 0.00653 0.00174 -0.0288 0.5115 0.8219
1.500 0.3929 0.00657 0.00178 -0.0290 0.5098 0.8244
1.750 0.4216 0.00661 0.00182 -0.0293 0.5081 0.8264
2.000 0.4504 0.00667 0.00186 -0.0296 0.5062 0.8279
2.250 0.4791 0.00673 0.00191 -0.0299 0.5042 0.8292
2.500 0.5082 0.00677 0.00196 -0.0303 0.5030 0.8305
2.750 0.5373 0.00680 0.00201 -0.0307 0.5013 0.8320
3.000 0.5663 0.00684 0.00206 -0.0311 0.4988 0.8334
3.250 0.5951 0.00690 0.00211 -0.0314 0.4958 0.8346
3.500 0.6238 0.00696 0.00217 -0.0317 0.4929 0.8359
3.750 0.6523 0.00703 0.00224 -0.0320 0.4902 0.8370
4.000 0.6809 0.00710 0.00231 -0.0324 0.4867 0.8381
4.250 0.7096 0.00714 0.00237 -0.0327 0.4816 0.8393
4.500 0.7375 0.00722 0.00244 -0.0329 0.4748 0.8407
4.750 0.7655 0.00728 0.00252 -0.0331 0.4661 0.8421
5.000 0.7927 0.00740 0.00262 -0.0332 0.4560 0.8437
5.250 0.8206 0.00748 0.00271 -0.0335 0.4454 0.8453
5.500 0.8471 0.00764 0.00283 -0.0335 0.4263 0.8469
5.750 0.8700 0.00805 0.00305 -0.0329 0.3813 0.8486
6.000 0.8885 0.00875 0.00349 -0.0318 0.3269 0.8505
6.250 0.9047 0.00957 0.00402 -0.0303 0.2690 0.8526
6.500 0.9178 0.01049 0.00463 -0.0284 0.2076 0.8548
6.750 0.9317 0.01125 0.00517 -0.0265 0.1626 0.8569
7.000 0.9422 0.01206 0.00576 -0.0241 0.1182 0.8596
7.250 0.9528 0.01277 0.00632 -0.0216 0.0878 0.8624
7.500 0.9640 0.01326 0.00677 -0.0192 0.0725 0.8655
7.750 0.9735 0.01375 0.00723 -0.0164 0.0616 0.8690
8.000 0.9800 0.01444 0.00785 -0.0134 0.0475 0.8726
8.250 0.9877 0.01512 0.00851 -0.0108 0.0376 0.8766
8.500 0.9975 0.01580 0.00919 -0.0086 0.0314 0.8806
8.750 1.0087 0.01649 0.00990 -0.0068 0.0278 0.8848
9.000 1.0214 0.01716 0.01058 -0.0053 0.0256 0.8887
9.250 1.0328 0.01789 0.01135 -0.0037 0.0238 0.8930
9.500 1.0443 0.01866 0.01216 -0.0022 0.0223 0.8981
9.750 1.0568 0.01944 0.01298 -0.0009 0.0209 0.9034
10.000 1.0673 0.02033 0.01391 0.0006 0.0193 0.9091
10.250 1.0782 0.02123 0.01486 0.0019 0.0181 0.9161
10.500 1.0898 0.02212 0.01580 0.0031 0.0173 0.9238
10.750 1.1006 0.02308 0.01682 0.0043 0.0165 0.9343
11.000 1.1134 0.02413 0.01794 0.0048 0.0155 0.9493
11.250 1.1377 0.02530 0.01918 0.0028 0.0141 0.9660
11.500 1.1578 0.02652 0.02044 0.0016 0.0132 1.0000
11.750 1.1676 0.02781 0.02175 0.0023 0.0125 1.0000
12.000 1.1778 0.02910 0.02306 0.0030 0.0121 1.0000
12.250 1.1881 0.03039 0.02439 0.0036 0.0116 1.0000
12.500 1.1977 0.03174 0.02578 0.0042 0.0113 1.0000
12.750 1.2067 0.03316 0.02724 0.0048 0.0109 1.0000
13.000 1.2153 0.03466 0.02877 0.0053 0.0104 1.0000
13.250 1.2236 0.03623 0.03037 0.0058 0.0101 1.0000
13.500 1.2309 0.03790 0.03208 0.0063 0.0099 1.0000
13.750 1.2392 0.03952 0.03374 0.0067 0.0096 1.0000
14.000 1.2474 0.04120 0.03547 0.0070 0.0095 1.0000
14.250 1.2557 0.04288 0.03720 0.0072 0.0092 1.0000
14.500 1.2631 0.04468 0.03906 0.0074 0.0091 1.0000
14.750 1.2706 0.04649 0.04091 0.0076 0.0089 1.0000
15.000 1.2766 0.04851 0.04299 0.0077 0.0089 1.0000
15.250 1.2833 0.05047 0.04500 0.0078 0.0087 1.0000
15.500 1.2888 0.05259 0.04718 0.0078 0.0087 1.0000
15.750 1.2948 0.05469 0.04933 0.0078 0.0085 1.0000
16.000 1.3000 0.05692 0.05163 0.0076 0.0084 1.0000
16.250 1.3050 0.05920 0.05395 0.0074 0.0082 1.0000
16.500 1.3092 0.06163 0.05644 0.0072 0.0081 1.0000
16.750 1.3120 0.06422 0.05910 0.0069 0.0081 1.0000
17.000 1.3156 0.06680 0.06173 0.0065 0.0080 1.0000
17.250 1.3179 0.06956 0.06456 0.0060 0.0080 1.0000
17.500 1.3188 0.07256 0.06763 0.0054 0.0078 1.0000
17.750 1.3176 0.07587 0.07102 0.0047 0.0077 1.0000
18.000 1.3167 0.07920 0.07443 0.0039 0.0076 1.0000
18.250 1.3168 0.08250 0.07781 0.0030 0.0076 1.0000
18.500 1.3180 0.08568 0.08106 0.0020 0.0076 1.0000
18.750 1.3156 0.08943 0.08490 0.0008 0.0075 1.0000
19.000 1.3140 0.09312 0.08867 -0.0004 0.0075 1.0000
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