NACA 64(2)-215 (naca642215-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(2)-215 (naca642215-il) Reynolds number: 50,000 Max Cl/Cd: 28.31 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca642215-il-50000.txt Download as CSV file: xf-naca642215-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5536 0.09246 0.08529 -0.0400 1.0000 0.1611
-10.500 -0.5741 0.08368 0.07654 -0.0451 1.0000 0.1519
-10.250 -0.6891 0.07305 0.06586 -0.0522 1.0000 0.1428
-10.000 -0.6946 0.06866 0.06145 -0.0517 1.0000 0.1407
-9.750 -0.7114 0.06453 0.05721 -0.0507 1.0000 0.1385
-9.500 -0.7303 0.06066 0.05315 -0.0489 1.0000 0.1362
-9.250 -0.7478 0.05708 0.04930 -0.0463 1.0000 0.1340
-9.000 -0.7625 0.05394 0.04583 -0.0430 1.0000 0.1322
-8.750 -0.7737 0.05127 0.04278 -0.0393 1.0000 0.1310
-8.500 -0.7747 0.04885 0.04016 -0.0362 1.0000 0.1316
-8.250 -0.7719 0.04670 0.03785 -0.0334 1.0000 0.1335
-8.000 -0.7689 0.04466 0.03560 -0.0306 1.0000 0.1355
-7.750 -0.7642 0.04263 0.03330 -0.0279 1.0000 0.1376
-7.500 -0.7564 0.04061 0.03097 -0.0254 1.0000 0.1395
-7.250 -0.7465 0.03877 0.02875 -0.0231 1.0000 0.1420
-7.000 -0.7324 0.03687 0.02676 -0.0214 1.0000 0.1468
-6.750 -0.7166 0.03537 0.02521 -0.0197 1.0000 0.1534
-6.500 -0.6997 0.03395 0.02354 -0.0179 1.0000 0.1596
-6.250 -0.6808 0.03259 0.02235 -0.0164 1.0000 0.1702
-6.000 -0.6626 0.03139 0.02127 -0.0147 1.0000 0.1830
-5.750 -0.6470 0.03024 0.02023 -0.0126 1.0000 0.2001
-5.500 -0.6360 0.02892 0.01916 -0.0103 1.0000 0.2259
-5.250 -0.6306 0.02702 0.01786 -0.0076 1.0000 0.2734
-5.000 -0.6394 0.02566 0.01868 -0.0004 1.0000 0.5093
-4.750 -0.6383 0.02863 0.02173 0.0092 1.0000 0.6117
-4.500 -0.6320 0.03080 0.02379 0.0166 1.0000 0.6550
-4.250 -0.6242 0.03268 0.02556 0.0237 1.0000 0.6878
-4.000 -0.6137 0.03452 0.02730 0.0305 1.0000 0.7173
-3.750 -0.5980 0.03640 0.02905 0.0369 1.0000 0.7476
-3.500 -0.5736 0.03829 0.03076 0.0420 1.0000 0.7831
-3.250 -0.4868 0.04122 0.03330 0.0384 1.0000 0.8297
-3.000 -0.4621 0.04111 0.03298 0.0383 1.0000 0.8510
-2.750 -0.4303 0.04090 0.03257 0.0364 1.0000 0.8677
-2.500 -0.3866 0.04070 0.03215 0.0320 0.9991 0.8813
-2.250 -0.3268 0.04065 0.03184 0.0241 0.9922 0.8927
-2.000 -0.2908 0.04044 0.03146 0.0201 0.9851 0.9027
-1.750 -0.2503 0.04028 0.03114 0.0154 0.9789 0.9119
-1.500 -0.2092 0.04016 0.03087 0.0105 0.9725 0.9202
-1.250 -0.1808 0.04003 0.03064 0.0079 0.9662 0.9288
-1.000 -0.1359 0.03999 0.03047 0.0023 0.9596 0.9363
-0.750 -0.1105 0.04002 0.03042 0.0001 0.9543 0.9445
-0.500 -0.0729 0.03995 0.03029 -0.0042 0.9487 0.9513
-0.250 -0.0393 0.04012 0.03039 -0.0079 0.9430 0.9590
0.000 -0.0019 0.04021 0.03043 -0.0123 0.9375 0.9660
0.250 0.0258 0.04035 0.03055 -0.0150 0.9326 0.9733
0.500 0.0728 0.04072 0.03088 -0.0212 0.9271 0.9807
0.750 0.1059 0.04096 0.03113 -0.0250 0.9218 0.9884
1.000 0.1413 0.04131 0.03148 -0.0293 0.9165 0.9963
1.250 0.1736 0.04181 0.03198 -0.0329 0.9110 1.0000
1.500 0.1672 0.04205 0.03223 -0.0298 0.9069 1.0000
1.750 0.1596 0.04222 0.03240 -0.0265 0.9031 1.0000
2.000 0.1563 0.04244 0.03261 -0.0239 0.8995 1.0000
2.250 0.1564 0.04273 0.03290 -0.0220 0.8962 1.0000
2.500 0.1542 0.04302 0.03319 -0.0196 0.8932 1.0000
2.750 0.1366 0.04292 0.03307 -0.0149 0.8928 1.0000
3.000 0.0984 0.04214 0.03226 -0.0072 0.8994 1.0000
3.250 0.0880 0.04215 0.03223 -0.0040 0.9044 1.0000
3.500 0.0983 0.04292 0.03297 -0.0041 0.9074 1.0000
3.750 0.1165 0.04413 0.03415 -0.0054 0.9097 1.0000
5.250 0.2813 0.05235 0.04260 -0.0171 0.8246 1.0000
5.500 0.3283 0.05380 0.04418 -0.0201 0.7930 1.0000
5.750 0.3511 0.05487 0.04533 -0.0205 0.7712 1.0000
6.000 0.4003 0.05610 0.04674 -0.0232 0.7434 1.0000
6.250 0.4199 0.05710 0.04784 -0.0230 0.7213 1.0000
6.500 0.4730 0.05781 0.04876 -0.0251 0.6947 1.0000
6.750 0.4896 0.05863 0.04970 -0.0242 0.6702 1.0000
7.000 0.5339 0.05861 0.04993 -0.0246 0.6419 1.0000
7.250 0.5869 0.05735 0.04896 -0.0243 0.6110 1.0000
7.500 0.6427 0.05454 0.04651 -0.0227 0.5769 1.0000
8.000 0.8426 0.02976 0.02255 -0.0073 0.3893 1.0000
8.250 0.8329 0.03136 0.02245 -0.0009 0.2730 1.0000
8.500 0.8360 0.03390 0.02421 0.0019 0.2231 1.0000
8.750 0.8647 0.03608 0.02600 0.0025 0.1862 1.0000
9.000 0.9231 0.03864 0.02826 -0.0003 0.1585 1.0000
9.250 0.9691 0.04141 0.03098 -0.0022 0.1443 1.0000
9.500 0.9938 0.04380 0.03365 -0.0019 0.1358 1.0000
9.750 1.0250 0.04708 0.03701 -0.0026 0.1297 1.0000
10.000 1.0372 0.04997 0.04037 -0.0011 0.1266 1.0000
10.250 1.0477 0.05295 0.04370 0.0002 0.1233 1.0000
10.500 1.0614 0.05603 0.04697 0.0011 0.1200 1.0000
10.750 1.0770 0.05985 0.05093 0.0015 0.1179 1.0000
11.000 1.0770 0.06363 0.05506 0.0032 0.1178 1.0000
11.250 1.0542 0.06699 0.05890 0.0064 0.1190 1.0000
11.500 1.0192 0.07057 0.06285 0.0098 0.1205 1.0000
11.750 0.9823 0.07519 0.06776 0.0112 0.1222 1.0000
12.000 0.9437 0.08090 0.07371 0.0107 0.1242 1.0000
12.250 0.9021 0.08809 0.08105 0.0082 0.1265 1.0000
12.500 0.8703 0.09600 0.08905 0.0048 0.1288 1.0000
12.750 0.8595 0.10295 0.09603 0.0023 0.1305 1.0000
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Polar data table (+)
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