NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 500,000 Max Cl/Cd: 71.42 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h15-il-500000-n5.txt Download as CSV file: xf-n5h15-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-15 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7020 0.05264 0.04904 -0.0525 0.7071 0.0208
-11.250 -0.8216 0.03902 0.03450 -0.0404 0.7054 0.0222
-11.000 -0.8353 0.03636 0.03150 -0.0352 0.7028 0.0225
-10.750 -0.8409 0.03422 0.02912 -0.0310 0.6999 0.0229
-10.500 -0.8326 0.03302 0.02780 -0.0286 0.6970 0.0232
-10.250 -0.8200 0.03222 0.02691 -0.0267 0.6942 0.0234
-10.000 -0.8065 0.03137 0.02595 -0.0249 0.6916 0.0236
-9.750 -0.7923 0.03047 0.02490 -0.0232 0.6891 0.0239
-9.500 -0.7761 0.02970 0.02404 -0.0217 0.6864 0.0242
-9.250 -0.7589 0.02897 0.02321 -0.0204 0.6834 0.0246
-9.000 -0.7418 0.02802 0.02210 -0.0190 0.6804 0.0250
-8.750 -0.7244 0.02690 0.02080 -0.0176 0.6774 0.0254
-8.500 -0.7063 0.02564 0.01933 -0.0163 0.6746 0.0258
-8.250 -0.6867 0.02445 0.01795 -0.0152 0.6718 0.0262
-8.000 -0.6655 0.02341 0.01675 -0.0143 0.6688 0.0267
-7.750 -0.6433 0.02256 0.01574 -0.0135 0.6659 0.0272
-7.500 -0.6202 0.02168 0.01469 -0.0129 0.6631 0.0275
-7.250 -0.5964 0.02082 0.01368 -0.0124 0.6604 0.0278
-6.750 -0.5468 0.01938 0.01200 -0.0117 0.6550 0.0282
-6.500 -0.5213 0.01874 0.01126 -0.0115 0.6522 0.0283
-6.250 -0.4954 0.01805 0.01048 -0.0113 0.6494 0.0285
-6.000 -0.4686 0.01694 0.00928 -0.0115 0.6468 0.0290
-5.750 -0.4429 0.01626 0.00854 -0.0113 0.6444 0.0295
-5.500 -0.4175 0.01579 0.00801 -0.0110 0.6422 0.0300
-5.250 -0.3920 0.01538 0.00759 -0.0108 0.6398 0.0305
-5.000 -0.3666 0.01498 0.00717 -0.0105 0.6368 0.0309
-4.750 -0.3414 0.01456 0.00671 -0.0102 0.6336 0.0313
-4.500 -0.3163 0.01420 0.00631 -0.0098 0.6307 0.0318
-4.250 -0.2916 0.01385 0.00591 -0.0093 0.6277 0.0321
-4.000 -0.2667 0.01352 0.00555 -0.0089 0.6247 0.0326
-3.750 -0.2417 0.01322 0.00523 -0.0085 0.6220 0.0331
-3.500 -0.2169 0.01293 0.00492 -0.0080 0.6191 0.0335
-3.250 -0.1921 0.01267 0.00462 -0.0075 0.6165 0.0341
-3.000 -0.1671 0.01244 0.00435 -0.0071 0.6139 0.0346
-2.750 -0.1421 0.01222 0.00409 -0.0066 0.6116 0.0350
-2.500 -0.1167 0.01202 0.00388 -0.0063 0.6090 0.0355
-2.250 -0.0915 0.01180 0.00365 -0.0059 0.6060 0.0362
-2.000 -0.0665 0.01157 0.00343 -0.0054 0.6031 0.0378
-1.750 -0.0410 0.01141 0.00326 -0.0051 0.6001 0.0395
-1.500 -0.0153 0.01127 0.00310 -0.0048 0.5972 0.0413
-1.250 0.0106 0.01115 0.00297 -0.0045 0.5944 0.0432
-1.000 0.0367 0.01102 0.00286 -0.0043 0.5910 0.0458
-0.750 0.0624 0.01088 0.00275 -0.0040 0.5874 0.0520
-0.500 0.0880 0.01076 0.00265 -0.0037 0.5839 0.0622
-0.250 0.1128 0.01059 0.00254 -0.0032 0.5806 0.0869
0.000 0.1304 0.00995 0.00243 -0.0016 0.5769 0.2470
0.250 0.1341 0.00879 0.00222 0.0027 0.5728 0.5094
0.500 0.1276 0.00769 0.00236 0.0103 0.5690 0.8305
0.750 0.1521 0.00782 0.00251 0.0112 0.5647 0.8616
1.000 0.1792 0.00792 0.00262 0.0114 0.5595 0.8747
1.250 0.2062 0.00805 0.00272 0.0117 0.5540 0.8852
1.500 0.2314 0.00822 0.00288 0.0124 0.5488 0.8977
1.750 0.2636 0.00848 0.00315 0.0117 0.5424 0.9077
2.000 0.2884 0.00858 0.00321 0.0123 0.5362 0.9134
2.250 0.3196 0.00866 0.00328 0.0115 0.5291 0.9152
2.500 0.3492 0.00875 0.00333 0.0109 0.5218 0.9170
2.750 0.3777 0.00882 0.00338 0.0106 0.5140 0.9188
3.000 0.4044 0.00891 0.00342 0.0106 0.5064 0.9209
3.250 0.4300 0.00897 0.00346 0.0108 0.4986 0.9230
3.500 0.4537 0.00903 0.00349 0.0114 0.4917 0.9250
3.750 0.4767 0.00908 0.00352 0.0121 0.4853 0.9269
4.000 0.5012 0.00915 0.00356 0.0125 0.4794 0.9284
4.250 0.5293 0.00925 0.00366 0.0121 0.4745 0.9295
4.500 0.5575 0.00935 0.00377 0.0117 0.4699 0.9305
4.750 0.5848 0.00947 0.00388 0.0115 0.4653 0.9316
5.000 0.6114 0.00960 0.00401 0.0113 0.4601 0.9328
5.250 0.6369 0.00977 0.00415 0.0114 0.4502 0.9342
5.500 0.6617 0.00993 0.00430 0.0116 0.4425 0.9357
5.750 0.6852 0.01012 0.00447 0.0120 0.4332 0.9376
6.000 0.7079 0.01028 0.00463 0.0126 0.4254 0.9399
6.250 0.7258 0.01049 0.00481 0.0141 0.4149 0.9429
6.500 0.7490 0.01066 0.00500 0.0145 0.4047 0.9446
6.750 0.7745 0.01089 0.00524 0.0144 0.3956 0.9460
7.000 0.7985 0.01118 0.00551 0.0145 0.3802 0.9476
7.250 0.8200 0.01155 0.00584 0.0149 0.3557 0.9498
7.500 0.8013 0.01303 0.00691 0.0214 0.2622 0.9590
7.750 0.8051 0.01530 0.00891 0.0214 0.2016 0.9641
8.000 0.8108 0.01730 0.01065 0.0215 0.1454 0.9691
8.250 0.8048 0.02045 0.01334 0.0216 0.0620 0.9742
8.500 0.8209 0.02185 0.01468 0.0209 0.0430 0.9765
8.750 0.8294 0.02371 0.01642 0.0208 0.0184 0.9802
9.000 0.8446 0.02481 0.01756 0.0208 0.0168 0.9838
9.250 0.8627 0.02607 0.01886 0.0199 0.0150 0.9857
9.500 0.8816 0.02718 0.02002 0.0192 0.0143 0.9879
9.750 0.8986 0.02840 0.02130 0.0186 0.0136 0.9907
10.000 0.9139 0.02972 0.02268 0.0182 0.0127 0.9937
10.250 0.9301 0.03115 0.02416 0.0175 0.0122 0.9973
10.500 0.9444 0.03287 0.02594 0.0166 0.0116 0.9993
10.750 0.9499 0.03436 0.02747 0.0177 0.0112 1.0000
11.000 0.9516 0.03555 0.02870 0.0200 0.0110 1.0000
11.250 0.9540 0.03692 0.03011 0.0219 0.0109 1.0000
11.500 0.9578 0.03834 0.03158 0.0235 0.0105 1.0000
11.750 0.9637 0.03971 0.03299 0.0249 0.0100 1.0000
12.000 0.9669 0.04139 0.03472 0.0261 0.0102 1.0000
12.250 0.9730 0.04289 0.03625 0.0272 0.0096 1.0000
12.500 0.9786 0.04451 0.03791 0.0281 0.0092 1.0000
12.750 0.9840 0.04620 0.03963 0.0289 0.0089 1.0000
13.000 0.9876 0.04812 0.04161 0.0298 0.0089 1.0000
13.250 0.9917 0.05002 0.04355 0.0305 0.0087 1.0000
13.500 0.9930 0.05225 0.04582 0.0312 0.0085 1.0000
13.750 0.9943 0.05452 0.04813 0.0319 0.0084 1.0000
14.000 0.9997 0.05645 0.05014 0.0324 0.0081 1.0000
14.250 1.0074 0.05817 0.05192 0.0326 0.0079 1.0000
14.500 1.0120 0.06024 0.05404 0.0330 0.0078 1.0000
14.750 1.0165 0.06233 0.05619 0.0334 0.0077 1.0000
15.000 1.0215 0.06441 0.05833 0.0336 0.0076 1.0000
15.250 1.0269 0.06645 0.06043 0.0338 0.0075 1.0000
15.500 1.0318 0.06858 0.06262 0.0340 0.0073 1.0000
15.750 1.0366 0.07072 0.06483 0.0342 0.0073 1.0000
16.000 1.0422 0.07288 0.06706 0.0341 0.0070 1.0000
16.250 1.0469 0.07513 0.06937 0.0341 0.0069 1.0000
16.500 1.0517 0.07739 0.07169 0.0340 0.0068 1.0000
16.750 1.0559 0.07976 0.07412 0.0339 0.0066 1.0000
17.000 1.0604 0.08219 0.07660 0.0335 0.0065 1.0000
17.250 1.0635 0.08479 0.07925 0.0331 0.0063 1.0000
17.500 1.0664 0.08734 0.08187 0.0328 0.0063 1.0000
17.750 1.0683 0.09003 0.08461 0.0326 0.0061 1.0000
18.000 1.0708 0.09271 0.08738 0.0321 0.0061 1.0000
18.250 1.0714 0.09552 0.09027 0.0319 0.0060 1.0000
18.500 1.0730 0.09846 0.09331 0.0313 0.0060 1.0000
18.750 1.0724 0.10179 0.09677 0.0304 0.0059 1.0000
19.000 1.0724 0.10497 0.10006 0.0297 0.0058 1.0000
19.250 1.0713 0.10839 0.10358 0.0288 0.0058 1.0000
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