NACA 1412 (naca1412-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 500,000 Max Cl/Cd: 66.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1412-il-500000-n5.txt Download as CSV file: xf-naca1412-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1412
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
------ -------- --------- --------- -------- -------- --------
-18.500 -0.9139 0.15280 0.15010 0.0146 1.0000 0.0153
-18.250 -0.9813 0.13333 0.13042 0.0039 1.0000 0.0153
-18.000 -1.0190 0.12143 0.11838 -0.0026 1.0000 0.0154
-17.750 -1.0557 0.11030 0.10710 -0.0086 1.0000 0.0154
-17.500 -1.0921 0.09963 0.09628 -0.0144 1.0000 0.0153
-17.250 -1.1284 0.08941 0.08592 -0.0200 1.0000 0.0153
-17.000 -1.1627 0.07982 0.07616 -0.0253 1.0000 0.0152
-16.750 -1.1930 0.07091 0.06708 -0.0304 1.0000 0.0152
-16.500 -1.2179 0.06292 0.05892 -0.0352 1.0000 0.0152
-16.250 -1.2364 0.05602 0.05187 -0.0396 1.0000 0.0153
-16.000 -1.2488 0.05029 0.04599 -0.0433 1.0000 0.0155
-15.750 -1.2563 0.04559 0.04115 -0.0462 1.0000 0.0157
-15.500 -1.2597 0.04178 0.03721 -0.0483 1.0000 0.0160
-15.250 -1.2603 0.03865 0.03395 -0.0496 1.0000 0.0163
-15.000 -1.2587 0.03606 0.03123 -0.0503 1.0000 0.0167
-14.750 -1.2552 0.03390 0.02896 -0.0504 1.0000 0.0171
-14.500 -1.2506 0.03207 0.02699 -0.0500 1.0000 0.0175
-14.250 -1.2445 0.03051 0.02530 -0.0491 1.0000 0.0180
-14.000 -1.2384 0.02909 0.02379 -0.0478 1.0000 0.0184
-13.750 -1.2302 0.02794 0.02258 -0.0464 1.0000 0.0189
-13.500 -1.2199 0.02702 0.02160 -0.0447 1.0000 0.0194
-13.250 -1.2085 0.02621 0.02071 -0.0430 1.0000 0.0200
-13.000 -1.1948 0.02541 0.01982 -0.0415 1.0000 0.0206
-12.750 -1.1793 0.02464 0.01895 -0.0402 1.0000 0.0213
-12.500 -1.1627 0.02391 0.01812 -0.0389 1.0000 0.0219
-12.250 -1.1462 0.02315 0.01728 -0.0377 1.0000 0.0225
-12.000 -1.1290 0.02244 0.01654 -0.0365 1.0000 0.0232
-11.750 -1.1101 0.02187 0.01590 -0.0354 1.0000 0.0239
-11.500 -1.0908 0.02131 0.01528 -0.0343 1.0000 0.0247
-11.250 -1.0716 0.02075 0.01465 -0.0332 1.0000 0.0254
-11.000 -1.0521 0.02022 0.01404 -0.0320 1.0000 0.0262
-10.750 -1.0322 0.01977 0.01350 -0.0308 1.0000 0.0268
-10.500 -1.0153 0.01906 0.01275 -0.0292 1.0000 0.0276
-10.250 -0.9969 0.01851 0.01218 -0.0278 1.0000 0.0284
-10.000 -0.9778 0.01805 0.01168 -0.0264 1.0000 0.0291
-9.750 -0.9584 0.01761 0.01120 -0.0250 1.0000 0.0300
-9.500 -0.9390 0.01720 0.01072 -0.0236 1.0000 0.0308
-9.250 -0.9195 0.01680 0.01027 -0.0222 1.0000 0.0316
-9.000 -0.8998 0.01644 0.00985 -0.0208 1.0000 0.0322
-8.750 -0.8821 0.01588 0.00927 -0.0191 1.0000 0.0332
-8.500 -0.8549 0.01538 0.00875 -0.0193 0.9986 0.0343
-8.250 -0.8234 0.01495 0.00828 -0.0204 0.9965 0.0354
-8.000 -0.7911 0.01455 0.00785 -0.0216 0.9945 0.0367
-7.750 -0.7596 0.01416 0.00741 -0.0226 0.9921 0.0377
-7.500 -0.7283 0.01378 0.00698 -0.0235 0.9892 0.0387
-7.250 -0.6964 0.01331 0.00651 -0.0246 0.9865 0.0406
-7.000 -0.6629 0.01293 0.00613 -0.0260 0.9843 0.0425
-6.750 -0.6310 0.01260 0.00576 -0.0270 0.9810 0.0444
-6.500 -0.5995 0.01228 0.00542 -0.0279 0.9769 0.0464
-6.250 -0.5670 0.01191 0.00507 -0.0290 0.9733 0.0501
-6.000 -0.5365 0.01162 0.00477 -0.0296 0.9683 0.0546
-5.750 -0.5066 0.01128 0.00448 -0.0301 0.9625 0.0618
-5.500 -0.4752 0.01097 0.00421 -0.0310 0.9577 0.0706
-5.250 -0.4473 0.01070 0.00396 -0.0310 0.9498 0.0797
-5.000 -0.4169 0.01043 0.00372 -0.0315 0.9435 0.0900
-4.500 -0.3612 0.00993 0.00329 -0.0314 0.9256 0.1141
-4.250 -0.3339 0.00969 0.00310 -0.0312 0.9152 0.1295
-4.000 -0.3068 0.00945 0.00291 -0.0310 0.9043 0.1470
-3.750 -0.2797 0.00923 0.00273 -0.0308 0.8929 0.1652
-3.500 -0.2528 0.00903 0.00257 -0.0305 0.8804 0.1841
-3.250 -0.2259 0.00884 0.00242 -0.0302 0.8668 0.2057
-3.000 -0.1995 0.00860 0.00228 -0.0298 0.8527 0.2384
-2.750 -0.1732 0.00838 0.00216 -0.0295 0.8377 0.2738
-2.500 -0.1465 0.00822 0.00204 -0.0292 0.8221 0.3022
-2.250 -0.1197 0.00807 0.00194 -0.0288 0.8058 0.3298
-2.000 -0.0929 0.00795 0.00185 -0.0285 0.7889 0.3560
-1.250 -0.0131 0.00762 0.00165 -0.0275 0.7346 0.4529
-1.000 0.0132 0.00750 0.00160 -0.0271 0.7151 0.4933
-0.750 0.0396 0.00742 0.00157 -0.0267 0.6948 0.5303
-0.500 0.0661 0.00736 0.00156 -0.0263 0.6744 0.5645
-0.250 0.0925 0.00732 0.00155 -0.0259 0.6547 0.5981
0.250 0.1454 0.00725 0.00157 -0.0251 0.6167 0.6649
0.500 0.1718 0.00722 0.00160 -0.0247 0.5977 0.6987
0.750 0.1980 0.00721 0.00164 -0.0242 0.5786 0.7309
1.500 0.2760 0.00731 0.00182 -0.0225 0.5176 0.8211
1.750 0.3021 0.00737 0.00190 -0.0219 0.4991 0.8482
2.000 0.3282 0.00745 0.00199 -0.0213 0.4810 0.8738
2.250 0.3546 0.00756 0.00210 -0.0208 0.4625 0.8967
2.500 0.3818 0.00772 0.00220 -0.0204 0.4414 0.9170
2.750 0.4103 0.00790 0.00232 -0.0204 0.4155 0.9346
3.250 0.4715 0.00830 0.00257 -0.0214 0.3709 0.9609
3.500 0.5024 0.00856 0.00271 -0.0221 0.3422 0.9708
3.750 0.5358 0.00886 0.00287 -0.0234 0.3103 0.9776
4.000 0.5673 0.00922 0.00306 -0.0244 0.2714 0.9844
4.250 0.6011 0.00964 0.00327 -0.0259 0.2314 0.9889
4.500 0.6336 0.01000 0.00349 -0.0271 0.2013 0.9936
4.750 0.6679 0.01034 0.00371 -0.0288 0.1758 0.9968
5.000 0.7013 0.01068 0.00396 -0.0302 0.1537 1.0000
5.250 0.7231 0.01098 0.00417 -0.0291 0.1366 1.0000
5.500 0.7449 0.01128 0.00440 -0.0280 0.1206 1.0000
5.750 0.7667 0.01161 0.00465 -0.0269 0.1055 1.0000
6.000 0.7885 0.01195 0.00492 -0.0258 0.0918 1.0000
6.250 0.8104 0.01229 0.00521 -0.0247 0.0801 1.0000
6.500 0.8325 0.01263 0.00550 -0.0237 0.0704 1.0000
6.750 0.8547 0.01299 0.00582 -0.0227 0.0616 1.0000
7.000 0.8770 0.01337 0.00616 -0.0217 0.0542 1.0000
7.250 0.8999 0.01372 0.00650 -0.0208 0.0493 1.0000
7.500 0.9225 0.01412 0.00688 -0.0200 0.0455 1.0000
7.750 0.9456 0.01447 0.00725 -0.0192 0.0430 1.0000
8.000 0.9683 0.01487 0.00765 -0.0183 0.0407 1.0000
8.250 0.9904 0.01534 0.00812 -0.0174 0.0387 1.0000
8.500 1.0132 0.01573 0.00856 -0.0166 0.0376 1.0000
8.750 1.0358 0.01615 0.00901 -0.0158 0.0366 1.0000
9.000 1.0580 0.01658 0.00949 -0.0150 0.0355 1.0000
9.250 1.0798 0.01705 0.00999 -0.0141 0.0344 1.0000
9.500 1.1007 0.01758 0.01054 -0.0131 0.0334 1.0000
9.750 1.1200 0.01823 0.01121 -0.0120 0.0323 1.0000
10.000 1.1405 0.01876 0.01180 -0.0109 0.0316 1.0000
10.250 1.1610 0.01926 0.01236 -0.0099 0.0309 1.0000
10.500 1.1808 0.01979 0.01296 -0.0088 0.0301 1.0000
10.750 1.1999 0.02036 0.01357 -0.0077 0.0293 1.0000
11.000 1.2181 0.02095 0.01422 -0.0065 0.0286 1.0000
11.250 1.2348 0.02162 0.01493 -0.0050 0.0278 1.0000
11.500 1.2474 0.02240 0.01575 -0.0030 0.0271 1.0000
11.750 1.2588 0.02325 0.01665 -0.0009 0.0265 1.0000
12.000 1.2736 0.02391 0.01740 0.0007 0.0260 1.0000
12.250 1.2873 0.02467 0.01825 0.0023 0.0254 1.0000
12.500 1.3002 0.02551 0.01917 0.0038 0.0248 1.0000
12.750 1.3125 0.02641 0.02014 0.0053 0.0242 1.0000
13.000 1.3245 0.02737 0.02117 0.0067 0.0236 1.0000
13.250 1.3352 0.02845 0.02231 0.0080 0.0230 1.0000
13.500 1.3435 0.02978 0.02370 0.0092 0.0224 1.0000
13.750 1.3481 0.03148 0.02546 0.0105 0.0219 1.0000
14.000 1.3576 0.03287 0.02697 0.0113 0.0216 1.0000
14.250 1.3658 0.03442 0.02864 0.0120 0.0211 1.0000
14.500 1.3730 0.03616 0.03049 0.0125 0.0206 1.0000
14.750 1.3794 0.03805 0.03248 0.0128 0.0201 1.0000
15.000 1.3849 0.04012 0.03465 0.0129 0.0196 1.0000
15.250 1.3896 0.04238 0.03700 0.0128 0.0191 1.0000
15.500 1.3924 0.04495 0.03965 0.0124 0.0187 1.0000
15.750 1.3925 0.04793 0.04272 0.0118 0.0183 1.0000
16.000 1.3893 0.05145 0.04635 0.0108 0.0180 1.0000
16.250 1.3865 0.05500 0.05002 0.0098 0.0177 1.0000
16.500 1.3823 0.05884 0.05400 0.0085 0.0174 1.0000
16.750 1.3767 0.06300 0.05829 0.0070 0.0171 1.0000
17.000 1.3690 0.06754 0.06296 0.0052 0.0168 1.0000
17.250 1.3600 0.07241 0.06796 0.0032 0.0166 1.0000
17.500 1.3493 0.07765 0.07333 0.0009 0.0163 1.0000
17.750 1.3371 0.08324 0.07905 -0.0016 0.0161 1.0000
18.000 1.3235 0.08918 0.08511 -0.0043 0.0159 1.0000
18.250 1.3086 0.09547 0.09152 -0.0073 0.0157 1.0000
18.500 1.2923 0.10210 0.09828 -0.0105 0.0156 1.0000
18.750 1.2755 0.10895 0.10524 -0.0139 0.0154 1.0000
19.000 1.2577 0.11614 0.11255 -0.0175 0.0153 1.0000
19.250 1.2398 0.12345 0.11997 -0.0214 0.0151 1.0000
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