NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 500,000 Max Cl/Cd: 92.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a415-il-500000-n5.txt Download as CSV file: xf-naca747a415-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8253 0.05990 0.05699 -0.0611 1.0000 0.0135
-14.500 -0.8635 0.05086 0.04767 -0.0669 1.0000 0.0135
-14.250 -0.8807 0.04627 0.04290 -0.0685 1.0000 0.0135
-14.000 -0.8906 0.04301 0.03950 -0.0686 1.0000 0.0136
-13.750 -0.8905 0.04067 0.03706 -0.0689 0.9624 0.0137
-13.500 -0.8818 0.03794 0.03407 -0.0711 0.9214 0.0139
-13.250 -0.8848 0.03611 0.03201 -0.0693 0.8935 0.0140
-13.000 -0.8882 0.03438 0.03006 -0.0669 0.8726 0.0141
-12.500 -0.8887 0.03131 0.02655 -0.0618 0.8393 0.0145
-12.250 -0.8855 0.02996 0.02500 -0.0593 0.8250 0.0147
-12.000 -0.8814 0.02862 0.02343 -0.0567 0.8113 0.0149
-11.750 -0.8750 0.02743 0.02201 -0.0542 0.7988 0.0151
-11.250 -0.8547 0.02532 0.01945 -0.0497 0.7764 0.0157
-11.000 -0.8396 0.02440 0.01831 -0.0482 0.7671 0.0159
-10.750 -0.8241 0.02348 0.01729 -0.0468 0.7578 0.0163
-10.500 -0.8062 0.02277 0.01648 -0.0456 0.7496 0.0165
-10.250 -0.7866 0.02223 0.01585 -0.0446 0.7415 0.0168
-10.000 -0.7669 0.02159 0.01509 -0.0437 0.7342 0.0171
-9.750 -0.7463 0.02093 0.01432 -0.0428 0.7267 0.0174
-9.500 -0.7253 0.02030 0.01355 -0.0419 0.7195 0.0179
-9.250 -0.7036 0.01962 0.01275 -0.0412 0.7129 0.0182
-9.000 -0.6815 0.01899 0.01199 -0.0404 0.7060 0.0186
-8.750 -0.6589 0.01844 0.01130 -0.0397 0.7000 0.0190
-8.500 -0.6363 0.01783 0.01062 -0.0391 0.6939 0.0195
-8.250 -0.6135 0.01731 0.01003 -0.0385 0.6878 0.0199
-8.000 -0.5899 0.01687 0.00955 -0.0380 0.6823 0.0204
-7.750 -0.5660 0.01643 0.00905 -0.0375 0.6764 0.0209
-7.500 -0.5422 0.01600 0.00853 -0.0369 0.6705 0.0213
-7.250 -0.5181 0.01557 0.00804 -0.0364 0.6653 0.0219
-7.000 -0.4938 0.01516 0.00756 -0.0359 0.6595 0.0224
-6.750 -0.4691 0.01482 0.00713 -0.0355 0.6538 0.0230
-6.500 -0.4454 0.01438 0.00666 -0.0349 0.6488 0.0238
-6.250 -0.4205 0.01405 0.00631 -0.0346 0.6434 0.0245
-6.000 -0.3955 0.01375 0.00596 -0.0342 0.6381 0.0254
-5.750 -0.3704 0.01346 0.00560 -0.0338 0.6332 0.0263
-5.500 -0.3449 0.01318 0.00527 -0.0334 0.6280 0.0271
-5.250 -0.3200 0.01286 0.00493 -0.0330 0.6226 0.0283
-5.000 -0.2945 0.01262 0.00465 -0.0327 0.6178 0.0296
-4.750 -0.2684 0.01240 0.00440 -0.0325 0.6131 0.0314
-4.500 -0.2425 0.01217 0.00414 -0.0322 0.6084 0.0334
-4.250 -0.2165 0.01196 0.00392 -0.0320 0.6040 0.0358
-4.000 -0.1901 0.01180 0.00371 -0.0318 0.6000 0.0384
-3.750 -0.1638 0.01158 0.00351 -0.0316 0.5959 0.0422
-3.500 -0.1372 0.01142 0.00334 -0.0315 0.5917 0.0467
-3.250 -0.1108 0.01126 0.00318 -0.0314 0.5878 0.0534
-3.000 -0.0844 0.01109 0.00302 -0.0312 0.5843 0.0620
-2.750 -0.0578 0.01091 0.00288 -0.0311 0.5807 0.0743
-2.500 -0.0318 0.01068 0.00274 -0.0309 0.5771 0.0983
-2.250 -0.0068 0.01035 0.00260 -0.0306 0.5736 0.1505
-2.000 0.0169 0.00992 0.00245 -0.0302 0.5704 0.2339
-1.750 0.0388 0.00933 0.00228 -0.0295 0.5676 0.3566
-1.500 0.0596 0.00863 0.00211 -0.0287 0.5647 0.5005
-1.250 0.0773 0.00783 0.00203 -0.0269 0.5618 0.6794
-1.000 0.1025 0.00780 0.00218 -0.0262 0.5588 0.7551
-0.750 0.1294 0.00789 0.00229 -0.0258 0.5558 0.7861
-0.500 0.1557 0.00806 0.00248 -0.0252 0.5531 0.8103
-0.250 0.1822 0.00823 0.00267 -0.0247 0.5507 0.8274
0.000 0.2098 0.00835 0.00277 -0.0245 0.5483 0.8365
0.250 0.2382 0.00839 0.00278 -0.0247 0.5459 0.8401
0.500 0.2665 0.00844 0.00282 -0.0248 0.5436 0.8426
0.750 0.2948 0.00849 0.00285 -0.0249 0.5414 0.8452
1.000 0.3232 0.00855 0.00288 -0.0251 0.5393 0.8477
1.250 0.3518 0.00860 0.00289 -0.0254 0.5374 0.8495
1.500 0.3805 0.00865 0.00292 -0.0257 0.5356 0.8513
1.750 0.4093 0.00869 0.00295 -0.0261 0.5339 0.8530
2.000 0.4382 0.00873 0.00298 -0.0264 0.5320 0.8546
2.250 0.4671 0.00877 0.00302 -0.0268 0.5299 0.8559
2.500 0.4955 0.00881 0.00307 -0.0271 0.5278 0.8571
2.750 0.5239 0.00887 0.00314 -0.0273 0.5261 0.8585
3.000 0.5522 0.00893 0.00322 -0.0276 0.5244 0.8599
3.250 0.5805 0.00901 0.00329 -0.0278 0.5226 0.8612
3.500 0.6086 0.00910 0.00337 -0.0281 0.5200 0.8626
3.750 0.6369 0.00914 0.00346 -0.0283 0.5170 0.8641
4.000 0.6652 0.00919 0.00355 -0.0286 0.5140 0.8656
4.250 0.6934 0.00926 0.00365 -0.0289 0.5113 0.8672
4.500 0.7215 0.00934 0.00374 -0.0292 0.5085 0.8688
4.750 0.7491 0.00944 0.00383 -0.0293 0.5043 0.8706
5.000 0.7770 0.00948 0.00393 -0.0296 0.4984 0.8724
5.250 0.8037 0.00954 0.00401 -0.0295 0.4911 0.8739
5.500 0.8303 0.00959 0.00410 -0.0295 0.4818 0.8754
5.750 0.8559 0.00969 0.00420 -0.0293 0.4706 0.8770
6.000 0.8819 0.00978 0.00432 -0.0292 0.4585 0.8788
6.250 0.9079 0.00989 0.00446 -0.0291 0.4459 0.8806
6.500 0.9320 0.01006 0.00461 -0.0287 0.4237 0.8827
6.750 0.9478 0.01064 0.00492 -0.0271 0.3645 0.8856
7.000 0.9566 0.01164 0.00559 -0.0245 0.3030 0.8889
7.250 0.9634 0.01259 0.00630 -0.0215 0.2486 0.8921
7.500 0.9681 0.01351 0.00702 -0.0182 0.2038 0.8964
7.750 0.9657 0.01441 0.00774 -0.0137 0.1652 0.9021
8.000 0.9654 0.01534 0.00854 -0.0098 0.1359 0.9074
8.250 0.9656 0.01634 0.00945 -0.0063 0.1107 0.9136
8.500 0.9684 0.01738 0.01042 -0.0035 0.0899 0.9204
8.750 0.9723 0.01842 0.01143 -0.0009 0.0746 0.9276
9.000 0.9779 0.01950 0.01249 0.0011 0.0607 0.9363
9.250 0.9850 0.02071 0.01368 0.0026 0.0469 0.9475
9.500 1.0006 0.02201 0.01496 0.0022 0.0374 0.9603
9.750 1.0231 0.02336 0.01632 0.0002 0.0311 0.9771
10.250 1.0447 0.02580 0.01881 0.0016 0.0257 1.0000
10.500 1.0552 0.02704 0.02007 0.0023 0.0242 1.0000
10.750 1.0643 0.02840 0.02145 0.0031 0.0229 1.0000
11.000 1.0742 0.02972 0.02282 0.0038 0.0217 1.0000
11.250 1.0841 0.03107 0.02421 0.0044 0.0203 1.0000
11.500 1.0933 0.03248 0.02565 0.0050 0.0193 1.0000
11.750 1.1001 0.03411 0.02730 0.0057 0.0183 1.0000
12.000 1.1097 0.03553 0.02879 0.0062 0.0177 1.0000
12.250 1.1186 0.03706 0.03037 0.0067 0.0168 1.0000
12.500 1.1264 0.03870 0.03206 0.0071 0.0163 1.0000
12.750 1.1339 0.04041 0.03380 0.0075 0.0156 1.0000
13.000 1.1404 0.04225 0.03568 0.0079 0.0150 1.0000
13.250 1.1475 0.04408 0.03757 0.0082 0.0147 1.0000
13.500 1.1547 0.04593 0.03949 0.0084 0.0142 1.0000
13.750 1.1618 0.04783 0.04145 0.0086 0.0138 1.0000
14.000 1.1683 0.04983 0.04351 0.0087 0.0135 1.0000
14.250 1.1746 0.05187 0.04560 0.0087 0.0131 1.0000
14.500 1.1805 0.05400 0.04779 0.0087 0.0129 1.0000
14.750 1.1856 0.05625 0.05009 0.0086 0.0126 1.0000
15.000 1.1887 0.05876 0.05266 0.0085 0.0124 1.0000
15.250 1.1914 0.06137 0.05533 0.0083 0.0121 1.0000
15.500 1.1967 0.06371 0.05775 0.0081 0.0120 1.0000
15.750 1.2009 0.06623 0.06036 0.0077 0.0117 1.0000
16.000 1.2057 0.06872 0.06292 0.0073 0.0115 1.0000
16.250 1.2095 0.07139 0.06567 0.0068 0.0113 1.0000
16.500 1.2122 0.07421 0.06857 0.0063 0.0111 1.0000
16.750 1.2138 0.07720 0.07165 0.0056 0.0111 1.0000
17.000 1.2171 0.08005 0.07457 0.0049 0.0109 1.0000
17.250 1.2181 0.08325 0.07786 0.0041 0.0108 1.0000
17.500 1.2206 0.08630 0.08099 0.0032 0.0106 1.0000
17.750 1.2213 0.08965 0.08442 0.0021 0.0105 1.0000
18.000 1.2216 0.09308 0.08793 0.0010 0.0104 1.0000
18.250 1.2220 0.09657 0.09151 -0.0002 0.0103 1.0000
18.500 1.2215 0.10027 0.09529 -0.0016 0.0102 1.0000
18.750 1.2205 0.10406 0.09917 -0.0031 0.0101 1.0000
19.000 1.2187 0.10803 0.10322 -0.0047 0.0100 1.0000
19.250 1.2171 0.11201 0.10729 -0.0064 0.0100 1.0000
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Polar data table (+)
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