NACA 1412 (naca1412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 500,000 Max Cl/Cd: 73.49 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1412-il-500000.txt Download as CSV file: xf-naca1412-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9855 0.10450 0.10157 -0.0138 1.0000 0.0216
-16.500 -1.0313 0.09142 0.08829 -0.0218 1.0000 0.0214
-16.250 -1.0647 0.08132 0.07800 -0.0282 1.0000 0.0214
-16.000 -1.0908 0.07287 0.06937 -0.0336 1.0000 0.0214
-15.750 -1.1114 0.06553 0.06185 -0.0384 1.0000 0.0215
-15.500 -1.1271 0.05922 0.05535 -0.0426 1.0000 0.0217
-15.250 -1.1388 0.05381 0.04974 -0.0462 1.0000 0.0219
-15.000 -1.1468 0.04926 0.04500 -0.0490 1.0000 0.0221
-14.750 -1.1578 0.04474 0.04030 -0.0511 1.0000 0.0224
-14.500 -1.1641 0.04117 0.03662 -0.0521 1.0000 0.0228
-14.250 -1.1617 0.03889 0.03428 -0.0525 1.0000 0.0232
-14.000 -1.1569 0.03707 0.03241 -0.0525 1.0000 0.0237
-13.750 -1.1515 0.03548 0.03073 -0.0520 1.0000 0.0242
-13.500 -1.1465 0.03400 0.02916 -0.0511 1.0000 0.0248
-13.250 -1.1415 0.03264 0.02766 -0.0497 1.0000 0.0254
-13.000 -1.1361 0.03141 0.02629 -0.0478 1.0000 0.0260
-12.750 -1.1293 0.03044 0.02517 -0.0455 1.0000 0.0266
-12.500 -1.1237 0.02866 0.02323 -0.0434 1.0000 0.0273
-12.250 -1.1121 0.02739 0.02193 -0.0419 1.0000 0.0281
-12.000 -1.0964 0.02667 0.02117 -0.0407 1.0000 0.0289
-11.750 -1.0798 0.02600 0.02044 -0.0394 1.0000 0.0298
-11.500 -1.0628 0.02530 0.01964 -0.0381 1.0000 0.0308
-11.250 -1.0450 0.02467 0.01889 -0.0369 1.0000 0.0317
-11.000 -1.0289 0.02368 0.01777 -0.0354 1.0000 0.0325
-10.750 -1.0146 0.02233 0.01638 -0.0338 1.0000 0.0337
-10.500 -0.9965 0.02172 0.01576 -0.0324 1.0000 0.0347
-10.250 -0.9780 0.02119 0.01519 -0.0310 1.0000 0.0358
-10.000 -0.9596 0.02065 0.01457 -0.0295 1.0000 0.0369
-9.750 -0.9407 0.02014 0.01398 -0.0281 1.0000 0.0378
-9.500 -0.9211 0.01978 0.01353 -0.0266 1.0000 0.0385
-9.250 -0.9080 0.01839 0.01211 -0.0245 1.0000 0.0400
-9.000 -0.8901 0.01783 0.01154 -0.0228 1.0000 0.0412
-8.750 -0.8717 0.01735 0.01103 -0.0212 1.0000 0.0423
-8.500 -0.8529 0.01690 0.01054 -0.0196 1.0000 0.0435
-8.250 -0.8339 0.01649 0.01007 -0.0181 1.0000 0.0447
-8.000 -0.8145 0.01612 0.00964 -0.0166 1.0000 0.0455
-7.750 -0.7975 0.01538 0.00886 -0.0147 1.0000 0.0468
-7.500 -0.7796 0.01479 0.00827 -0.0131 1.0000 0.0485
-7.250 -0.7599 0.01441 0.00787 -0.0117 1.0000 0.0499
-7.000 -0.7398 0.01405 0.00748 -0.0104 1.0000 0.0514
-6.750 -0.7095 0.01369 0.00709 -0.0111 0.9987 0.0533
-6.500 -0.6739 0.01316 0.00652 -0.0130 0.9963 0.0560
-6.250 -0.6374 0.01270 0.00608 -0.0150 0.9942 0.0598
-6.000 -0.6018 0.01237 0.00572 -0.0167 0.9913 0.0637
-5.750 -0.5667 0.01187 0.00528 -0.0185 0.9881 0.0723
-5.500 -0.5301 0.01144 0.00492 -0.0205 0.9856 0.0863
-5.250 -0.4925 0.01100 0.00459 -0.0228 0.9836 0.1059
-5.000 -0.4594 0.01064 0.00432 -0.0240 0.9791 0.1255
-4.750 -0.4231 0.01029 0.00407 -0.0259 0.9758 0.1476
-4.500 -0.3850 0.00994 0.00382 -0.0282 0.9735 0.1733
-4.250 -0.3475 0.00958 0.00360 -0.0304 0.9711 0.2027
-4.000 -0.3168 0.00926 0.00340 -0.0310 0.9646 0.2321
-3.750 -0.2824 0.00893 0.00320 -0.0324 0.9603 0.2642
-3.500 -0.2528 0.00865 0.00303 -0.0327 0.9533 0.2945
-3.250 -0.2226 0.00836 0.00286 -0.0331 0.9463 0.3278
-3.000 -0.1953 0.00806 0.00271 -0.0329 0.9374 0.3691
-2.750 -0.1675 0.00775 0.00256 -0.0327 0.9289 0.4145
-2.500 -0.1420 0.00749 0.00245 -0.0321 0.9173 0.4538
-2.250 -0.1157 0.00726 0.00233 -0.0315 0.9062 0.4940
-2.000 -0.0893 0.00706 0.00223 -0.0310 0.8946 0.5325
-1.750 -0.0634 0.00687 0.00214 -0.0303 0.8812 0.5701
-1.500 -0.0375 0.00671 0.00208 -0.0296 0.8667 0.6100
-1.250 -0.0117 0.00655 0.00202 -0.0289 0.8515 0.6501
-1.000 0.0140 0.00642 0.00198 -0.0281 0.8353 0.6899
-0.750 0.0398 0.00633 0.00195 -0.0274 0.8182 0.7261
-0.500 0.0656 0.00627 0.00193 -0.0266 0.8003 0.7595
-0.250 0.0913 0.00622 0.00193 -0.0258 0.7821 0.7913
0.000 0.1171 0.00620 0.00195 -0.0250 0.7632 0.8214
0.250 0.1428 0.00621 0.00198 -0.0241 0.7437 0.8500
0.500 0.1683 0.00626 0.00201 -0.0232 0.7238 0.8769
0.750 0.1941 0.00634 0.00207 -0.0223 0.7036 0.8996
1.000 0.2205 0.00645 0.00213 -0.0216 0.6828 0.9197
1.250 0.2482 0.00658 0.00219 -0.0212 0.6602 0.9367
1.500 0.2778 0.00673 0.00226 -0.0212 0.6376 0.9505
1.750 0.3094 0.00689 0.00234 -0.0218 0.6160 0.9619
2.000 0.3422 0.00706 0.00243 -0.0226 0.5940 0.9719
2.500 0.4181 0.00745 0.00261 -0.0268 0.5450 0.9835
2.750 0.4590 0.00765 0.00270 -0.0296 0.5186 0.9874
3.000 0.4981 0.00782 0.00279 -0.0320 0.4952 0.9925
3.250 0.5378 0.00802 0.00288 -0.0347 0.4683 0.9962
3.500 0.5774 0.00823 0.00298 -0.0373 0.4390 0.9999
3.750 0.6007 0.00841 0.00305 -0.0365 0.4103 1.0000
4.000 0.6232 0.00862 0.00313 -0.0356 0.3801 1.0000
4.250 0.6456 0.00885 0.00324 -0.0346 0.3517 1.0000
4.500 0.6678 0.00909 0.00338 -0.0336 0.3247 1.0000
5.000 0.7114 0.00968 0.00372 -0.0314 0.2680 1.0000
5.250 0.7330 0.01001 0.00393 -0.0303 0.2402 1.0000
5.500 0.7544 0.01037 0.00416 -0.0291 0.2126 1.0000
5.750 0.7755 0.01076 0.00442 -0.0279 0.1852 1.0000
6.000 0.7966 0.01118 0.00471 -0.0267 0.1594 1.0000
6.250 0.8179 0.01159 0.00501 -0.0256 0.1366 1.0000
6.500 0.8387 0.01206 0.00535 -0.0244 0.1148 1.0000
6.750 0.8599 0.01252 0.00572 -0.0232 0.0952 1.0000
7.000 0.8805 0.01307 0.00616 -0.0220 0.0778 1.0000
7.250 0.9015 0.01362 0.00664 -0.0208 0.0664 1.0000
7.500 0.9234 0.01408 0.00710 -0.0198 0.0603 1.0000
7.750 0.9443 0.01466 0.00764 -0.0186 0.0555 1.0000
8.000 0.9663 0.01513 0.00815 -0.0176 0.0530 1.0000
8.250 0.9885 0.01559 0.00865 -0.0167 0.0509 1.0000
8.500 1.0100 0.01610 0.00918 -0.0157 0.0490 1.0000
8.750 1.0294 0.01680 0.00988 -0.0144 0.0470 1.0000
9.000 1.0482 0.01754 0.01067 -0.0131 0.0455 1.0000
9.250 1.0694 0.01805 0.01125 -0.0121 0.0445 1.0000
9.500 1.0899 0.01861 0.01187 -0.0110 0.0433 1.0000
9.750 1.1099 0.01919 0.01248 -0.0099 0.0421 1.0000
10.000 1.1290 0.01982 0.01314 -0.0087 0.0409 1.0000
10.250 1.1455 0.02066 0.01401 -0.0072 0.0397 1.0000
10.500 1.1568 0.02202 0.01541 -0.0050 0.0384 1.0000
10.750 1.1759 0.02255 0.01602 -0.0038 0.0378 1.0000
11.000 1.1924 0.02320 0.01675 -0.0023 0.0369 1.0000
11.250 1.2070 0.02390 0.01753 -0.0005 0.0360 1.0000
11.500 1.2209 0.02464 0.01833 0.0012 0.0350 1.0000
11.750 1.2340 0.02545 0.01918 0.0030 0.0341 1.0000
12.000 1.2451 0.02646 0.02022 0.0047 0.0333 1.0000
12.250 1.2511 0.02821 0.02202 0.0069 0.0323 1.0000
12.500 1.2617 0.02935 0.02327 0.0085 0.0317 1.0000
12.750 1.2731 0.03033 0.02437 0.0099 0.0310 1.0000
13.000 1.2832 0.03147 0.02561 0.0112 0.0302 1.0000
13.250 1.2923 0.03274 0.02697 0.0124 0.0294 1.0000
13.500 1.3006 0.03413 0.02844 0.0134 0.0287 1.0000
13.750 1.3080 0.03566 0.03002 0.0143 0.0281 1.0000
14.000 1.3134 0.03747 0.03187 0.0151 0.0275 1.0000
14.250 1.3111 0.04038 0.03486 0.0164 0.0266 1.0000
14.500 1.3158 0.04231 0.03695 0.0166 0.0262 1.0000
14.750 1.3191 0.04453 0.03932 0.0165 0.0257 1.0000
15.000 1.3212 0.04702 0.04194 0.0163 0.0251 1.0000
15.250 1.3220 0.04976 0.04481 0.0159 0.0246 1.0000
15.500 1.3221 0.05268 0.04784 0.0152 0.0240 1.0000
15.750 1.3215 0.05578 0.05103 0.0143 0.0236 1.0000
16.000 1.3204 0.05904 0.05437 0.0133 0.0232 1.0000
16.250 1.3180 0.06251 0.05791 0.0121 0.0228 1.0000
16.500 1.3132 0.06636 0.06183 0.0108 0.0225 1.0000
16.750 1.3014 0.07115 0.06672 0.0096 0.0220 1.0000
17.000 1.2897 0.07638 0.07212 0.0073 0.0218 1.0000
17.250 1.2792 0.08177 0.07768 0.0045 0.0216 1.0000
17.500 1.2670 0.08758 0.08366 0.0015 0.0214 1.0000
17.750 1.2529 0.09385 0.09009 -0.0018 0.0211 1.0000
18.000 1.2371 0.10059 0.09699 -0.0055 0.0209 1.0000
18.250 1.2196 0.10784 0.10440 -0.0095 0.0207 1.0000
18.500 1.2001 0.11567 0.11239 -0.0139 0.0205 1.0000
18.750 1.1776 0.12436 0.12125 -0.0189 0.0204 1.0000
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