NACA 0015 (naca0015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0015 (naca0015-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.88 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0015-il-1000000.txt Download as CSV file: xf-naca0015-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2970 0.09858 0.09490 -0.0142 1.0000 0.0253
-19.500 -1.3072 0.09342 0.08964 -0.0166 1.0000 0.0255
-19.250 -1.3172 0.08835 0.08447 -0.0189 1.0000 0.0257
-19.000 -1.3264 0.08347 0.07949 -0.0210 1.0000 0.0259
-18.750 -1.3346 0.07874 0.07466 -0.0231 1.0000 0.0260
-18.500 -1.3416 0.07426 0.07008 -0.0250 1.0000 0.0261
-18.250 -1.3528 0.06938 0.06509 -0.0269 1.0000 0.0263
-18.000 -1.3680 0.06409 0.05971 -0.0288 1.0000 0.0266
-17.750 -1.3805 0.05922 0.05476 -0.0306 1.0000 0.0268
-17.500 -1.3899 0.05483 0.05028 -0.0321 1.0000 0.0271
-17.250 -1.3961 0.05093 0.04629 -0.0333 1.0000 0.0273
-17.000 -1.3996 0.04745 0.04273 -0.0343 1.0000 0.0276
-16.750 -1.4005 0.04438 0.03958 -0.0351 1.0000 0.0278
-16.500 -1.3991 0.04163 0.03675 -0.0356 1.0000 0.0281
-16.250 -1.3963 0.03912 0.03418 -0.0360 1.0000 0.0285
-16.000 -1.3920 0.03686 0.03184 -0.0362 1.0000 0.0288
-15.750 -1.3864 0.03481 0.02971 -0.0362 1.0000 0.0292
-15.500 -1.3796 0.03295 0.02777 -0.0360 1.0000 0.0295
-15.250 -1.3718 0.03127 0.02602 -0.0356 1.0000 0.0298
-15.000 -1.3622 0.02981 0.02448 -0.0351 1.0000 0.0300
-14.750 -1.3558 0.02817 0.02276 -0.0344 1.0000 0.0304
-14.500 -1.3544 0.02625 0.02078 -0.0330 1.0000 0.0309
-14.250 -1.3476 0.02486 0.01934 -0.0317 1.0000 0.0314
-14.000 -1.3376 0.02375 0.01819 -0.0304 1.0000 0.0319
-13.750 -1.3257 0.02283 0.01722 -0.0291 1.0000 0.0324
-13.500 -1.3132 0.02199 0.01633 -0.0277 1.0000 0.0329
-13.250 -1.3000 0.02122 0.01551 -0.0262 1.0000 0.0334
-13.000 -1.2858 0.02055 0.01479 -0.0247 1.0000 0.0339
-12.750 -1.2704 0.01997 0.01416 -0.0232 1.0000 0.0344
-12.500 -1.2573 0.01931 0.01345 -0.0213 1.0000 0.0349
-12.250 -1.2479 0.01854 0.01265 -0.0187 1.0000 0.0357
-12.000 -1.2357 0.01797 0.01206 -0.0163 1.0000 0.0364
-11.750 -1.2206 0.01748 0.01154 -0.0143 1.0000 0.0372
-11.500 -1.2037 0.01704 0.01107 -0.0126 1.0000 0.0379
-11.250 -1.1862 0.01665 0.01065 -0.0110 1.0000 0.0387
-11.000 -1.1686 0.01632 0.01028 -0.0092 1.0000 0.0394
-10.750 -1.1553 0.01580 0.00974 -0.0067 1.0000 0.0407
-10.500 -1.1406 0.01538 0.00932 -0.0044 1.0000 0.0419
-10.250 -1.1251 0.01503 0.00896 -0.0022 1.0000 0.0431
-10.000 -1.1092 0.01474 0.00865 0.0000 1.0000 0.0444
-9.750 -1.0944 0.01439 0.00828 0.0024 1.0000 0.0459
-9.500 -1.0800 0.01402 0.00793 0.0048 1.0000 0.0481
-9.250 -1.0641 0.01374 0.00764 0.0070 1.0000 0.0503
-9.000 -1.0379 0.01333 0.00726 0.0070 0.9991 0.0541
-8.750 -1.0050 0.01295 0.00689 0.0057 0.9975 0.0588
-8.500 -0.9719 0.01255 0.00654 0.0043 0.9959 0.0649
-8.250 -0.9383 0.01216 0.00619 0.0028 0.9944 0.0722
-8.000 -0.9039 0.01179 0.00588 0.0012 0.9931 0.0799
-7.750 -0.8723 0.01144 0.00558 0.0002 0.9906 0.0878
-7.500 -0.8394 0.01112 0.00529 -0.0011 0.9880 0.0960
-7.250 -0.8054 0.01080 0.00503 -0.0025 0.9858 0.1046
-7.000 -0.7707 0.01046 0.00475 -0.0042 0.9841 0.1153
-6.750 -0.7355 0.01012 0.00448 -0.0059 0.9825 0.1270
-6.500 -0.7028 0.00981 0.00424 -0.0071 0.9796 0.1395
-6.250 -0.6737 0.00951 0.00401 -0.0074 0.9742 0.1529
-6.000 -0.6430 0.00921 0.00378 -0.0080 0.9697 0.1677
-5.750 -0.6153 0.00894 0.00358 -0.0080 0.9633 0.1821
-5.500 -0.5885 0.00869 0.00338 -0.0077 0.9559 0.1968
-5.250 -0.5623 0.00845 0.00320 -0.0073 0.9477 0.2124
-5.000 -0.5364 0.00822 0.00303 -0.0067 0.9387 0.2292
-4.750 -0.5108 0.00800 0.00287 -0.0062 0.9285 0.2475
-4.500 -0.4850 0.00778 0.00271 -0.0057 0.9183 0.2690
-4.250 -0.4591 0.00758 0.00257 -0.0051 0.9062 0.2895
-4.000 -0.4328 0.00740 0.00244 -0.0047 0.8938 0.3080
-3.750 -0.4063 0.00725 0.00231 -0.0043 0.8806 0.3258
-3.500 -0.3798 0.00711 0.00219 -0.0039 0.8664 0.3441
-3.250 -0.3530 0.00698 0.00209 -0.0035 0.8510 0.3619
-3.000 -0.3261 0.00687 0.00200 -0.0032 0.8353 0.3805
-2.750 -0.2990 0.00677 0.00191 -0.0029 0.8188 0.3986
-2.500 -0.2720 0.00668 0.00183 -0.0026 0.8018 0.4171
-2.250 -0.2450 0.00660 0.00176 -0.0023 0.7844 0.4366
-2.000 -0.2179 0.00653 0.00169 -0.0020 0.7660 0.4562
-1.750 -0.1908 0.00647 0.00164 -0.0017 0.7474 0.4763
-1.500 -0.1636 0.00642 0.00159 -0.0015 0.7280 0.4961
-1.250 -0.1364 0.00638 0.00155 -0.0012 0.7086 0.5153
-1.000 -0.1091 0.00636 0.00152 -0.0009 0.6892 0.5343
-0.750 -0.0819 0.00634 0.00150 -0.0007 0.6693 0.5530
-0.500 -0.0546 0.00633 0.00148 -0.0005 0.6497 0.5721
-0.250 -0.0273 0.00632 0.00147 -0.0002 0.6302 0.5913
0.250 0.0273 0.00632 0.00147 0.0002 0.5912 0.6302
0.500 0.0546 0.00633 0.00148 0.0005 0.5720 0.6498
0.750 0.0819 0.00634 0.00150 0.0007 0.5531 0.6691
1.000 0.1091 0.00635 0.00152 0.0009 0.5345 0.6891
1.250 0.1364 0.00638 0.00155 0.0012 0.5153 0.7086
1.500 0.1636 0.00642 0.00159 0.0015 0.4962 0.7282
1.750 0.1908 0.00647 0.00164 0.0017 0.4761 0.7475
2.000 0.2179 0.00653 0.00169 0.0020 0.4561 0.7660
2.250 0.2450 0.00660 0.00176 0.0023 0.4366 0.7843
2.500 0.2720 0.00668 0.00183 0.0026 0.4171 0.8019
2.750 0.2990 0.00677 0.00191 0.0029 0.3986 0.8189
3.000 0.3260 0.00687 0.00200 0.0032 0.3804 0.8353
3.250 0.3530 0.00698 0.00209 0.0035 0.3619 0.8510
3.500 0.3798 0.00711 0.00219 0.0039 0.3441 0.8663
3.750 0.4063 0.00725 0.00231 0.0043 0.3259 0.8806
4.000 0.4328 0.00740 0.00244 0.0047 0.3079 0.8938
4.250 0.4591 0.00758 0.00257 0.0051 0.2896 0.9062
4.500 0.4850 0.00778 0.00271 0.0056 0.2691 0.9183
4.750 0.5108 0.00800 0.00287 0.0062 0.2474 0.9285
5.000 0.5364 0.00822 0.00303 0.0067 0.2292 0.9387
5.250 0.5623 0.00845 0.00320 0.0073 0.2123 0.9477
5.500 0.5885 0.00869 0.00338 0.0077 0.1967 0.9558
5.750 0.6153 0.00894 0.00358 0.0080 0.1820 0.9633
6.000 0.6431 0.00921 0.00378 0.0080 0.1677 0.9697
6.250 0.6738 0.00951 0.00400 0.0074 0.1530 0.9743
6.500 0.7028 0.00980 0.00424 0.0071 0.1395 0.9797
6.750 0.7355 0.01012 0.00448 0.0059 0.1269 0.9825
7.000 0.7708 0.01046 0.00475 0.0041 0.1152 0.9841
7.250 0.8055 0.01080 0.00502 0.0025 0.1045 0.9859
7.500 0.8395 0.01112 0.00529 0.0010 0.0959 0.9880
7.750 0.8723 0.01144 0.00558 -0.0002 0.0877 0.9906
8.000 0.9040 0.01179 0.00588 -0.0012 0.0799 0.9931
8.250 0.9384 0.01216 0.00619 -0.0028 0.0722 0.9944
8.500 0.9720 0.01255 0.00654 -0.0043 0.0649 0.9959
8.750 1.0051 0.01295 0.00689 -0.0057 0.0588 0.9976
9.000 1.0381 0.01333 0.00725 -0.0071 0.0541 0.9992
9.250 1.0639 0.01374 0.00764 -0.0070 0.0503 1.0000
9.500 1.0799 0.01402 0.00793 -0.0048 0.0481 1.0000
9.750 1.0943 0.01439 0.00828 -0.0024 0.0459 1.0000
10.000 1.1091 0.01473 0.00864 0.0000 0.0444 1.0000
10.250 1.1251 0.01503 0.00896 0.0022 0.0431 1.0000
10.500 1.1405 0.01538 0.00932 0.0044 0.0419 1.0000
10.750 1.1554 0.01579 0.00974 0.0067 0.0407 1.0000
11.000 1.1687 0.01631 0.01028 0.0092 0.0394 1.0000
11.250 1.1864 0.01665 0.01065 0.0109 0.0387 1.0000
11.500 1.2039 0.01704 0.01107 0.0126 0.0379 1.0000
11.750 1.2210 0.01748 0.01154 0.0143 0.0372 1.0000
12.000 1.2362 0.01797 0.01206 0.0162 0.0364 1.0000
12.250 1.2485 0.01854 0.01265 0.0185 0.0357 1.0000
12.500 1.2579 0.01932 0.01346 0.0212 0.0349 1.0000
12.750 1.2712 0.01997 0.01416 0.0230 0.0344 1.0000
13.000 1.2867 0.02054 0.01478 0.0245 0.0339 1.0000
13.250 1.3008 0.02122 0.01551 0.0260 0.0334 1.0000
13.500 1.3142 0.02198 0.01632 0.0275 0.0329 1.0000
13.750 1.3268 0.02282 0.01721 0.0289 0.0324 1.0000
14.000 1.3387 0.02375 0.01819 0.0302 0.0319 1.0000
14.250 1.3488 0.02485 0.01932 0.0315 0.0314 1.0000
14.500 1.3558 0.02624 0.02076 0.0328 0.0309 1.0000
14.750 1.3567 0.02819 0.02278 0.0342 0.0303 1.0000
15.000 1.3640 0.02976 0.02443 0.0349 0.0300 1.0000
15.250 1.3736 0.03123 0.02597 0.0354 0.0298 1.0000
15.500 1.3816 0.03289 0.02772 0.0357 0.0295 1.0000
15.750 1.3883 0.03476 0.02966 0.0359 0.0292 1.0000
16.000 1.3941 0.03680 0.03178 0.0359 0.0288 1.0000
16.250 1.3985 0.03906 0.03411 0.0357 0.0285 1.0000
16.500 1.4016 0.04153 0.03665 0.0354 0.0281 1.0000
16.750 1.4029 0.04430 0.03950 0.0348 0.0278 1.0000
17.000 1.4022 0.04736 0.04263 0.0340 0.0275 1.0000
17.250 1.3986 0.05084 0.04620 0.0330 0.0273 1.0000
17.500 1.3925 0.05475 0.05019 0.0318 0.0270 1.0000
17.750 1.3830 0.05916 0.05469 0.0302 0.0268 1.0000
18.000 1.3704 0.06405 0.05967 0.0285 0.0265 1.0000
18.250 1.3550 0.06937 0.06509 0.0265 0.0263 1.0000
18.500 1.3453 0.07406 0.06988 0.0246 0.0261 1.0000
18.750 1.3383 0.07856 0.07448 0.0227 0.0260 1.0000
19.000 1.3300 0.08330 0.07932 0.0207 0.0258 1.0000
19.250 1.3208 0.08819 0.08431 0.0185 0.0257 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0015 (naca0015-il)