NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A315 (naca747a315-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.34 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a315-il-1000000-n5.txt Download as CSV file: xf-naca747a315-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0914 0.07060 0.06790 -0.0425 1.0000 0.0104
-17.500 -1.1235 0.06078 0.05788 -0.0492 1.0000 0.0104
-17.250 -1.1455 0.05392 0.05083 -0.0533 1.0000 0.0104
-17.000 -1.1603 0.04895 0.04571 -0.0554 1.0000 0.0104
-16.750 -1.1709 0.04502 0.04163 -0.0564 1.0000 0.0104
-16.500 -1.1769 0.04193 0.03841 -0.0565 1.0000 0.0105
-16.250 -1.1781 0.03952 0.03589 -0.0562 1.0000 0.0106
-16.000 -1.1809 0.03709 0.03333 -0.0555 1.0000 0.0107
-15.750 -1.1768 0.03538 0.03152 -0.0547 1.0000 0.0107
-15.500 -1.1733 0.03367 0.02970 -0.0537 1.0000 0.0108
-15.000 -1.1693 0.03001 0.02582 -0.0512 0.9633 0.0110
-14.750 -1.1562 0.02867 0.02427 -0.0512 0.9138 0.0112
-14.500 -1.1524 0.02758 0.02301 -0.0488 0.8857 0.0113
-14.250 -1.1449 0.02665 0.02194 -0.0468 0.8641 0.0114
-14.000 -1.1351 0.02583 0.02101 -0.0449 0.8455 0.0115
-13.750 -1.1243 0.02505 0.02010 -0.0431 0.8283 0.0117
-13.500 -1.1121 0.02435 0.01929 -0.0414 0.8127 0.0118
-13.250 -1.0991 0.02368 0.01851 -0.0397 0.7988 0.0120
-13.000 -1.0859 0.02300 0.01773 -0.0380 0.7861 0.0122
-12.750 -1.0724 0.02234 0.01695 -0.0363 0.7739 0.0123
-12.500 -1.0583 0.02169 0.01620 -0.0346 0.7631 0.0125
-12.250 -1.0434 0.02110 0.01549 -0.0329 0.7530 0.0127
-12.000 -1.0283 0.02049 0.01479 -0.0312 0.7432 0.0128
-11.750 -1.0124 0.01996 0.01415 -0.0295 0.7345 0.0130
-11.500 -0.9964 0.01942 0.01351 -0.0278 0.7262 0.0131
-11.250 -0.9788 0.01895 0.01294 -0.0263 0.7189 0.0133
-11.000 -0.9594 0.01847 0.01238 -0.0251 0.7120 0.0134
-10.750 -0.9406 0.01788 0.01170 -0.0239 0.7055 0.0136
-10.500 -0.9210 0.01730 0.01106 -0.0228 0.6999 0.0138
-10.250 -0.8999 0.01684 0.01054 -0.0219 0.6936 0.0141
-10.000 -0.8781 0.01642 0.01006 -0.0211 0.6876 0.0143
-9.750 -0.8551 0.01607 0.00967 -0.0205 0.6821 0.0147
-9.500 -0.8323 0.01569 0.00923 -0.0198 0.6759 0.0149
-9.250 -0.8092 0.01532 0.00880 -0.0191 0.6701 0.0152
-9.000 -0.7859 0.01495 0.00837 -0.0185 0.6645 0.0155
-8.750 -0.7622 0.01460 0.00797 -0.0179 0.6583 0.0157
-8.500 -0.7383 0.01427 0.00756 -0.0174 0.6527 0.0160
-8.250 -0.7140 0.01394 0.00719 -0.0169 0.6472 0.0162
-8.000 -0.6896 0.01364 0.00682 -0.0164 0.6411 0.0164
-7.750 -0.6658 0.01327 0.00641 -0.0158 0.6355 0.0169
-7.500 -0.6411 0.01295 0.00607 -0.0154 0.6299 0.0174
-7.250 -0.6161 0.01268 0.00575 -0.0150 0.6239 0.0178
-7.000 -0.5909 0.01243 0.00546 -0.0146 0.6189 0.0182
-6.750 -0.5653 0.01218 0.00518 -0.0143 0.6140 0.0188
-6.500 -0.5396 0.01195 0.00491 -0.0140 0.6089 0.0193
-6.000 -0.4881 0.01148 0.00438 -0.0134 0.5999 0.0204
-5.750 -0.4622 0.01126 0.00415 -0.0132 0.5952 0.0213
-5.500 -0.4359 0.01108 0.00394 -0.0130 0.5905 0.0224
-5.250 -0.4094 0.01091 0.00374 -0.0128 0.5863 0.0234
-5.000 -0.3830 0.01072 0.00354 -0.0127 0.5823 0.0248
-4.750 -0.3564 0.01054 0.00336 -0.0125 0.5779 0.0263
-4.500 -0.3296 0.01040 0.00319 -0.0124 0.5736 0.0280
-4.250 -0.3029 0.01024 0.00302 -0.0123 0.5698 0.0302
-4.000 -0.2759 0.01009 0.00288 -0.0122 0.5662 0.0326
-3.750 -0.2489 0.00995 0.00273 -0.0121 0.5623 0.0354
-3.500 -0.2219 0.00982 0.00260 -0.0121 0.5585 0.0390
-3.000 -0.1676 0.00955 0.00236 -0.0120 0.5520 0.0500
-2.750 -0.1404 0.00942 0.00225 -0.0120 0.5487 0.0581
-2.500 -0.1135 0.00926 0.00214 -0.0119 0.5453 0.0711
-2.250 -0.0871 0.00906 0.00203 -0.0118 0.5418 0.0961
-2.000 -0.0615 0.00881 0.00192 -0.0115 0.5386 0.1406
-1.750 -0.0362 0.00848 0.00181 -0.0113 0.5363 0.2017
-1.500 -0.0113 0.00813 0.00170 -0.0110 0.5338 0.2721
-1.250 0.0123 0.00768 0.00157 -0.0105 0.5313 0.3682
-1.000 0.0363 0.00726 0.00146 -0.0100 0.5288 0.4608
-0.750 0.0594 0.00680 0.00134 -0.0094 0.5264 0.5611
-0.500 0.0781 0.00614 0.00131 -0.0077 0.5241 0.7395
-0.250 0.1052 0.00615 0.00141 -0.0075 0.5221 0.7783
0.000 0.1334 0.00620 0.00149 -0.0075 0.5204 0.7973
0.250 0.1620 0.00625 0.00154 -0.0076 0.5186 0.8070
0.500 0.1908 0.00629 0.00159 -0.0079 0.5167 0.8125
0.750 0.2199 0.00634 0.00162 -0.0082 0.5148 0.8162
1.000 0.2490 0.00638 0.00163 -0.0085 0.5130 0.8186
1.250 0.2781 0.00642 0.00165 -0.0088 0.5112 0.8208
1.500 0.3069 0.00646 0.00169 -0.0091 0.5092 0.8232
1.750 0.3357 0.00651 0.00173 -0.0094 0.5072 0.8253
2.000 0.3648 0.00655 0.00177 -0.0098 0.5058 0.8268
2.250 0.3940 0.00658 0.00181 -0.0102 0.5046 0.8280
2.500 0.4231 0.00661 0.00186 -0.0105 0.5031 0.8294
2.750 0.4522 0.00665 0.00190 -0.0109 0.5008 0.8308
3.000 0.4812 0.00670 0.00195 -0.0113 0.4976 0.8322
3.250 0.5100 0.00676 0.00200 -0.0116 0.4944 0.8334
3.500 0.5387 0.00683 0.00206 -0.0120 0.4916 0.8346
3.750 0.5676 0.00688 0.00212 -0.0123 0.4886 0.8357
4.000 0.5966 0.00692 0.00217 -0.0127 0.4837 0.8367
4.250 0.6249 0.00699 0.00223 -0.0130 0.4767 0.8380
4.500 0.6533 0.00704 0.00230 -0.0133 0.4685 0.8394
4.750 0.6809 0.00714 0.00238 -0.0134 0.4585 0.8409
5.000 0.7090 0.00722 0.00247 -0.0137 0.4462 0.8424
5.250 0.7365 0.00734 0.00256 -0.0138 0.4310 0.8439
5.500 0.7619 0.00762 0.00271 -0.0137 0.3955 0.8455
5.750 0.7802 0.00843 0.00318 -0.0126 0.3239 0.8474
6.000 0.7992 0.00915 0.00364 -0.0116 0.2685 0.8493
6.250 0.8142 0.01007 0.00423 -0.0101 0.2014 0.8514
6.500 0.8304 0.01082 0.00473 -0.0087 0.1538 0.8533
6.750 0.8452 0.01155 0.00526 -0.0070 0.1112 0.8555
7.000 0.8612 0.01212 0.00572 -0.0055 0.0849 0.8578
7.250 0.8786 0.01257 0.00612 -0.0041 0.0694 0.8602
7.500 0.8936 0.01308 0.00656 -0.0024 0.0544 0.8629
7.750 0.9040 0.01358 0.00701 0.0001 0.0411 0.8662
8.000 0.9132 0.01409 0.00750 0.0029 0.0343 0.8697
8.250 0.9241 0.01462 0.00804 0.0051 0.0300 0.8730
8.500 0.9352 0.01520 0.00863 0.0072 0.0268 0.8766
8.750 0.9482 0.01575 0.00922 0.0088 0.0249 0.8804
9.000 0.9604 0.01640 0.00989 0.0105 0.0231 0.8844
9.500 0.9857 0.01774 0.01130 0.0134 0.0202 0.8926
9.750 0.9974 0.01851 0.01210 0.0148 0.0190 0.8977
10.000 1.0093 0.01932 0.01295 0.0161 0.0180 0.9029
10.250 1.0212 0.02012 0.01380 0.0174 0.0166 0.9085
10.500 1.0326 0.02099 0.01472 0.0186 0.0159 0.9157
10.750 1.0428 0.02196 0.01573 0.0199 0.0148 0.9239
11.000 1.0547 0.02287 0.01671 0.0209 0.0142 0.9344
11.250 1.0694 0.02388 0.01780 0.0211 0.0135 0.9482
11.500 1.0936 0.02502 0.01901 0.0192 0.0130 0.9620
11.750 1.1213 0.02635 0.02037 0.0161 0.0123 0.9754
12.000 1.1341 0.02765 0.02171 0.0162 0.0118 1.0000
12.250 1.1447 0.02888 0.02298 0.0168 0.0113 1.0000
12.500 1.1549 0.03015 0.02429 0.0174 0.0112 1.0000
12.750 1.1643 0.03152 0.02569 0.0180 0.0107 1.0000
13.000 1.1735 0.03290 0.02712 0.0185 0.0106 1.0000
13.250 1.1824 0.03435 0.02860 0.0190 0.0104 1.0000
13.500 1.1906 0.03590 0.03019 0.0195 0.0102 1.0000
13.750 1.1989 0.03747 0.03179 0.0199 0.0100 1.0000
14.000 1.2047 0.03929 0.03366 0.0203 0.0097 1.0000
14.250 1.2105 0.04115 0.03556 0.0206 0.0095 1.0000
14.500 1.2183 0.04289 0.03736 0.0208 0.0094 1.0000
14.750 1.2262 0.04463 0.03914 0.0210 0.0094 1.0000
15.000 1.2326 0.04654 0.04112 0.0211 0.0093 1.0000
15.250 1.2388 0.04851 0.04315 0.0212 0.0092 1.0000
15.500 1.2457 0.05045 0.04514 0.0212 0.0091 1.0000
15.750 1.2507 0.05261 0.04737 0.0211 0.0090 1.0000
16.000 1.2563 0.05472 0.04954 0.0210 0.0088 1.0000
16.250 1.2615 0.05694 0.05182 0.0208 0.0087 1.0000
16.500 1.2646 0.05942 0.05436 0.0206 0.0086 1.0000
16.750 1.2693 0.06177 0.05677 0.0203 0.0086 1.0000
17.000 1.2735 0.06419 0.05926 0.0199 0.0085 1.0000
17.250 1.2751 0.06696 0.06209 0.0194 0.0084 1.0000
17.500 1.2773 0.06971 0.06491 0.0189 0.0083 1.0000
17.750 1.2796 0.07252 0.06778 0.0182 0.0081 1.0000
18.000 1.2815 0.07540 0.07074 0.0175 0.0081 1.0000
18.250 1.2811 0.07863 0.07405 0.0167 0.0081 1.0000
18.500 1.2806 0.08193 0.07742 0.0157 0.0080 1.0000
18.750 1.2800 0.08532 0.08089 0.0147 0.0079 1.0000
19.000 1.2773 0.08909 0.08474 0.0134 0.0079 1.0000
19.250 1.2760 0.09270 0.08843 0.0121 0.0078 1.0000
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