NACA 2415 (n2415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 500,000 Max Cl/Cd: 79.24 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2415-il-500000-n5.txt Download as CSV file: xf-n2415-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2415
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
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0663 0.08368 0.07937 -0.0473 1.0000 0.0240
-17.500 -1.0875 0.07693 0.07252 -0.0509 1.0000 0.0241
-17.250 -1.1091 0.07023 0.06571 -0.0545 1.0000 0.0242
-17.000 -1.1291 0.06377 0.05912 -0.0581 1.0000 0.0243
-16.750 -1.1462 0.05770 0.05294 -0.0615 1.0000 0.0245
-16.500 -1.1596 0.05222 0.04733 -0.0647 1.0000 0.0247
-16.250 -1.1691 0.04741 0.04240 -0.0675 1.0000 0.0249
-16.000 -1.1749 0.04325 0.03813 -0.0698 1.0000 0.0251
-15.750 -1.1776 0.03972 0.03448 -0.0716 1.0000 0.0254
-15.500 -1.1777 0.03674 0.03139 -0.0729 1.0000 0.0257
-15.250 -1.1759 0.03421 0.02876 -0.0736 1.0000 0.0260
-15.000 -1.1725 0.03207 0.02652 -0.0738 1.0000 0.0264
-14.750 -1.1679 0.03027 0.02462 -0.0734 1.0000 0.0268
-14.500 -1.1622 0.02875 0.02300 -0.0726 1.0000 0.0272
-14.250 -1.1556 0.02747 0.02163 -0.0714 1.0000 0.0276
-14.000 -1.1522 0.02620 0.02030 -0.0695 1.0000 0.0280
-13.750 -1.1484 0.02520 0.01925 -0.0670 1.0000 0.0284
-13.500 -1.1466 0.02442 0.01843 -0.0636 1.0000 0.0288
-13.250 -1.1466 0.02380 0.01776 -0.0595 1.0000 0.0293
-13.000 -1.1409 0.02319 0.01710 -0.0562 1.0000 0.0299
-12.750 -1.1342 0.02264 0.01650 -0.0530 1.0000 0.0305
-12.500 -1.1266 0.02213 0.01592 -0.0498 1.0000 0.0311
-12.250 -1.1084 0.02148 0.01521 -0.0488 0.9989 0.0318
-12.000 -1.0815 0.02074 0.01445 -0.0495 0.9966 0.0327
-11.750 -1.0533 0.02010 0.01377 -0.0503 0.9945 0.0337
-11.500 -1.0245 0.01952 0.01313 -0.0512 0.9925 0.0348
-11.250 -0.9970 0.01900 0.01253 -0.0516 0.9896 0.0358
-11.000 -0.9690 0.01837 0.01190 -0.0523 0.9868 0.0371
-10.750 -0.9390 0.01785 0.01135 -0.0533 0.9846 0.0385
-10.500 -0.9075 0.01738 0.01083 -0.0544 0.9829 0.0400
-10.250 -0.8777 0.01687 0.01030 -0.0553 0.9805 0.0415
-10.000 -0.8502 0.01640 0.00981 -0.0556 0.9765 0.0431
-9.750 -0.8203 0.01598 0.00936 -0.0563 0.9733 0.0449
-9.500 -0.7895 0.01554 0.00889 -0.0572 0.9706 0.0468
-9.250 -0.7606 0.01512 0.00847 -0.0577 0.9669 0.0490
-9.000 -0.7336 0.01477 0.00809 -0.0576 0.9614 0.0512
-8.750 -0.7045 0.01436 0.00768 -0.0581 0.9572 0.0536
-8.500 -0.6755 0.01401 0.00731 -0.0585 0.9528 0.0565
-8.250 -0.6497 0.01369 0.00697 -0.0581 0.9460 0.0591
-8.000 -0.6212 0.01334 0.00662 -0.0583 0.9407 0.0625
-7.750 -0.5948 0.01305 0.00631 -0.0581 0.9336 0.0658
-7.500 -0.5680 0.01273 0.00599 -0.0579 0.9260 0.0697
-7.250 -0.5410 0.01247 0.00570 -0.0576 0.9184 0.0735
-7.000 -0.5147 0.01217 0.00541 -0.0573 0.9098 0.0783
-6.750 -0.4878 0.01193 0.00515 -0.0571 0.9020 0.0830
-6.500 -0.4614 0.01167 0.00489 -0.0567 0.8931 0.0885
-6.250 -0.4345 0.01144 0.00465 -0.0565 0.8848 0.0943
-6.000 -0.4078 0.01121 0.00442 -0.0562 0.8751 0.1010
-5.750 -0.3810 0.01099 0.00420 -0.0559 0.8659 0.1080
-5.500 -0.3541 0.01080 0.00400 -0.0556 0.8556 0.1156
-5.250 -0.3272 0.01060 0.00380 -0.0554 0.8455 0.1247
-5.000 -0.3004 0.01042 0.00361 -0.0551 0.8345 0.1343
-4.750 -0.2734 0.01024 0.00344 -0.0548 0.8232 0.1444
-4.250 -0.2195 0.00994 0.00313 -0.0543 0.7995 0.1675
-4.000 -0.1924 0.00979 0.00299 -0.0540 0.7872 0.1799
-3.750 -0.1654 0.00966 0.00286 -0.0538 0.7749 0.1930
-3.500 -0.1384 0.00955 0.00274 -0.0535 0.7615 0.2069
-3.250 -0.1113 0.00943 0.00263 -0.0533 0.7483 0.2221
-3.000 -0.0842 0.00933 0.00254 -0.0530 0.7350 0.2383
-2.500 -0.0302 0.00916 0.00237 -0.0525 0.7072 0.2720
-2.250 -0.0031 0.00908 0.00230 -0.0522 0.6932 0.2899
-1.750 0.0508 0.00895 0.00219 -0.0517 0.6656 0.3288
-1.500 0.0776 0.00889 0.00214 -0.0514 0.6511 0.3498
-1.250 0.1046 0.00882 0.00211 -0.0512 0.6373 0.3720
-1.000 0.1314 0.00876 0.00208 -0.0509 0.6235 0.3970
-0.750 0.1581 0.00870 0.00206 -0.0506 0.6102 0.4249
-0.500 0.1846 0.00864 0.00206 -0.0503 0.5964 0.4564
-0.250 0.2113 0.00857 0.00206 -0.0500 0.5834 0.4904
0.000 0.2379 0.00852 0.00208 -0.0497 0.5708 0.5236
0.250 0.2643 0.00850 0.00210 -0.0493 0.5585 0.5563
0.500 0.2910 0.00846 0.00214 -0.0490 0.5462 0.5893
0.750 0.3176 0.00844 0.00218 -0.0486 0.5348 0.6200
1.250 0.3705 0.00842 0.00229 -0.0478 0.5118 0.6809
1.500 0.3968 0.00844 0.00236 -0.0474 0.5010 0.7105
1.750 0.4230 0.00845 0.00243 -0.0469 0.4895 0.7411
2.000 0.4491 0.00846 0.00252 -0.0464 0.4788 0.7707
2.250 0.4747 0.00852 0.00262 -0.0457 0.4677 0.8006
2.500 0.5007 0.00855 0.00272 -0.0451 0.4569 0.8296
2.750 0.5263 0.00862 0.00284 -0.0444 0.4465 0.8575
3.000 0.5521 0.00871 0.00296 -0.0438 0.4352 0.8831
3.250 0.5786 0.00882 0.00309 -0.0433 0.4239 0.9062
3.500 0.6061 0.00898 0.00323 -0.0430 0.4117 0.9262
3.750 0.6354 0.00916 0.00337 -0.0432 0.3978 0.9427
4.000 0.6661 0.00934 0.00352 -0.0438 0.3828 0.9565
4.250 0.6990 0.00956 0.00368 -0.0448 0.3672 0.9699
4.500 0.7328 0.00980 0.00385 -0.0461 0.3511 0.9812
4.750 0.7685 0.01006 0.00404 -0.0480 0.3333 0.9868
5.000 0.8011 0.01034 0.00423 -0.0491 0.3155 0.9919
5.250 0.8347 0.01063 0.00444 -0.0505 0.2972 0.9955
5.500 0.8677 0.01095 0.00466 -0.0519 0.2780 0.9992
5.750 0.8899 0.01125 0.00487 -0.0509 0.2607 1.0000
6.000 0.9089 0.01153 0.00508 -0.0493 0.2447 1.0000
6.250 0.9280 0.01183 0.00530 -0.0476 0.2292 1.0000
6.500 0.9472 0.01214 0.00554 -0.0460 0.2143 1.0000
6.750 0.9665 0.01247 0.00581 -0.0445 0.1994 1.0000
7.000 0.9861 0.01282 0.00608 -0.0430 0.1853 1.0000
7.250 1.0059 0.01319 0.00638 -0.0416 0.1711 1.0000
7.500 1.0257 0.01357 0.00671 -0.0402 0.1579 1.0000
7.750 1.0455 0.01397 0.00704 -0.0389 0.1453 1.0000
8.000 1.0651 0.01439 0.00740 -0.0375 0.1341 1.0000
8.250 1.0844 0.01483 0.00779 -0.0361 0.1235 1.0000
8.500 1.1036 0.01526 0.00817 -0.0348 0.1139 1.0000
8.750 1.1228 0.01568 0.00857 -0.0334 0.1059 1.0000
9.000 1.1403 0.01613 0.00899 -0.0317 0.0988 1.0000
9.250 1.1568 0.01659 0.00943 -0.0299 0.0920 1.0000
9.500 1.1736 0.01706 0.00989 -0.0282 0.0862 1.0000
9.750 1.1895 0.01760 0.01041 -0.0264 0.0806 1.0000
10.000 1.2064 0.01810 0.01092 -0.0249 0.0758 1.0000
10.250 1.2219 0.01870 0.01151 -0.0232 0.0713 1.0000
10.500 1.2382 0.01927 0.01209 -0.0217 0.0672 1.0000
10.750 1.2528 0.01994 0.01276 -0.0200 0.0635 1.0000
11.000 1.2685 0.02058 0.01343 -0.0186 0.0602 1.0000
11.250 1.2821 0.02136 0.01421 -0.0170 0.0570 1.0000
11.500 1.2968 0.02208 0.01497 -0.0156 0.0543 1.0000
11.750 1.3100 0.02293 0.01583 -0.0141 0.0516 1.0000
12.000 1.3227 0.02384 0.01677 -0.0127 0.0494 1.0000
12.250 1.3357 0.02475 0.01772 -0.0114 0.0473 1.0000
12.500 1.3469 0.02581 0.01881 -0.0100 0.0454 1.0000
12.750 1.3578 0.02695 0.01999 -0.0088 0.0438 1.0000
13.000 1.3691 0.02809 0.02119 -0.0077 0.0422 1.0000
13.250 1.3788 0.02938 0.02253 -0.0066 0.0406 1.0000
13.500 1.3864 0.03089 0.02407 -0.0055 0.0392 1.0000
13.750 1.3959 0.03231 0.02556 -0.0046 0.0381 1.0000
14.000 1.4041 0.03388 0.02720 -0.0038 0.0368 1.0000
14.250 1.4107 0.03564 0.02901 -0.0031 0.0357 1.0000
14.500 1.4155 0.03763 0.03105 -0.0024 0.0348 1.0000
14.750 1.4204 0.03968 0.03317 -0.0019 0.0340 1.0000
15.000 1.4255 0.04175 0.03534 -0.0015 0.0331 1.0000
15.250 1.4293 0.04403 0.03769 -0.0013 0.0323 1.0000
15.500 1.4317 0.04653 0.04026 -0.0012 0.0315 1.0000
15.750 1.4324 0.04929 0.04309 -0.0012 0.0308 1.0000
16.250 1.4318 0.05526 0.04923 -0.0017 0.0295 1.0000
16.500 1.4315 0.05835 0.05241 -0.0021 0.0289 1.0000
16.750 1.4298 0.06167 0.05582 -0.0026 0.0283 1.0000
17.000 1.4268 0.06520 0.05944 -0.0033 0.0278 1.0000
17.250 1.4225 0.06898 0.06331 -0.0042 0.0273 1.0000
17.500 1.4166 0.07303 0.06745 -0.0052 0.0269 1.0000
17.750 1.4091 0.07738 0.07189 -0.0064 0.0265 1.0000
18.000 1.4010 0.08184 0.07644 -0.0076 0.0261 1.0000
18.250 1.3950 0.08609 0.08079 -0.0089 0.0258 1.0000
18.500 1.3882 0.09051 0.08532 -0.0103 0.0254 1.0000
18.750 1.3806 0.09510 0.09001 -0.0119 0.0250 1.0000
19.000 1.3724 0.09981 0.09483 -0.0136 0.0247 1.0000
19.250 1.3637 0.10468 0.09979 -0.0154 0.0243 1.0000
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