NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-215 AIRFOIL (n63215-il) Reynolds number: 500,000 Max Cl/Cd: 73.64 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63215-il-500000-n5.txt Download as CSV file: xf-n63215-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-215 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-19.000 -0.9568 0.12473 0.12158 -0.0095 1.0000 0.0131
-18.750 -0.9806 0.11534 0.11202 -0.0151 1.0000 0.0131
-18.500 -0.9999 0.10715 0.10367 -0.0199 1.0000 0.0132
-18.250 -1.0161 0.09988 0.09626 -0.0241 1.0000 0.0132
-18.000 -1.0300 0.09322 0.08946 -0.0280 1.0000 0.0133
-17.750 -1.0426 0.08706 0.08316 -0.0314 1.0000 0.0133
-17.500 -1.0520 0.08157 0.07754 -0.0344 1.0000 0.0135
-17.250 -1.0600 0.07651 0.07236 -0.0371 1.0000 0.0135
-17.000 -1.0671 0.07179 0.06750 -0.0395 1.0000 0.0136
-16.750 -1.0724 0.06746 0.06304 -0.0416 1.0000 0.0138
-16.500 -1.0766 0.06345 0.05889 -0.0435 1.0000 0.0139
-16.250 -1.0791 0.05983 0.05515 -0.0450 1.0000 0.0140
-16.000 -1.0809 0.05640 0.05162 -0.0463 1.0000 0.0141
-15.750 -1.0838 0.05298 0.04812 -0.0476 1.0000 0.0143
-15.500 -1.0853 0.04986 0.04493 -0.0486 1.0000 0.0145
-15.250 -1.0841 0.04718 0.04217 -0.0493 1.0000 0.0146
-15.000 -1.0819 0.04467 0.03959 -0.0499 1.0000 0.0148
-14.750 -1.0784 0.04239 0.03723 -0.0504 1.0000 0.0150
-14.500 -1.0726 0.04036 0.03514 -0.0507 1.0000 0.0154
-14.250 -1.0667 0.03842 0.03312 -0.0508 1.0000 0.0156
-14.000 -1.0607 0.03653 0.03115 -0.0509 1.0000 0.0159
-13.750 -1.0540 0.03476 0.02930 -0.0508 1.0000 0.0161
-13.500 -1.0466 0.03308 0.02755 -0.0506 1.0000 0.0165
-13.250 -1.0387 0.03151 0.02589 -0.0503 1.0000 0.0167
-13.000 -1.0303 0.03002 0.02432 -0.0499 1.0000 0.0170
-12.750 -1.0206 0.02867 0.02289 -0.0494 1.0000 0.0172
-12.500 -1.0137 0.02716 0.02133 -0.0487 1.0000 0.0176
-12.250 -1.0045 0.02587 0.02000 -0.0481 1.0000 0.0179
-12.000 -0.9937 0.02476 0.01886 -0.0473 1.0000 0.0183
-11.750 -0.9819 0.02377 0.01782 -0.0465 1.0000 0.0188
-11.500 -0.9696 0.02287 0.01688 -0.0456 1.0000 0.0193
-11.250 -0.9581 0.02197 0.01594 -0.0445 1.0000 0.0198
-11.000 -0.9466 0.02117 0.01509 -0.0432 1.0000 0.0204
-10.750 -0.9158 0.02026 0.01407 -0.0456 0.9557 0.0210
-10.500 -0.8925 0.01934 0.01307 -0.0465 0.9253 0.0218
-10.250 -0.8786 0.01880 0.01243 -0.0449 0.9022 0.0224
-10.000 -0.8623 0.01831 0.01184 -0.0435 0.8855 0.0231
-9.750 -0.8449 0.01782 0.01126 -0.0423 0.8719 0.0239
-9.500 -0.8260 0.01737 0.01072 -0.0412 0.8601 0.0248
-9.250 -0.8066 0.01692 0.01017 -0.0403 0.8492 0.0257
-9.000 -0.7869 0.01640 0.00961 -0.0394 0.8390 0.0269
-8.750 -0.7656 0.01599 0.00913 -0.0387 0.8301 0.0281
-8.500 -0.7431 0.01560 0.00868 -0.0381 0.8210 0.0293
-8.250 -0.7201 0.01525 0.00823 -0.0376 0.8130 0.0304
-8.000 -0.6975 0.01479 0.00774 -0.0370 0.8047 0.0319
-7.750 -0.6741 0.01442 0.00731 -0.0366 0.7972 0.0334
-7.500 -0.6496 0.01407 0.00692 -0.0363 0.7894 0.0351
-7.250 -0.6247 0.01379 0.00655 -0.0360 0.7821 0.0368
-7.000 -0.6000 0.01340 0.00616 -0.0358 0.7750 0.0394
-6.750 -0.5747 0.01310 0.00582 -0.0356 0.7676 0.0424
-6.500 -0.5492 0.01279 0.00548 -0.0354 0.7609 0.0463
-6.250 -0.5233 0.01248 0.00516 -0.0353 0.7538 0.0518
-6.000 -0.4977 0.01216 0.00483 -0.0351 0.7472 0.0598
-5.750 -0.4715 0.01183 0.00453 -0.0351 0.7403 0.0713
-5.500 -0.4457 0.01146 0.00422 -0.0350 0.7337 0.0889
-5.250 -0.4198 0.01107 0.00391 -0.0350 0.7273 0.1145
-5.000 -0.3938 0.01065 0.00361 -0.0350 0.7204 0.1471
-4.500 -0.3418 0.00974 0.00301 -0.0351 0.7080 0.2353
-4.250 -0.3159 0.00922 0.00272 -0.0352 0.7013 0.2978
-4.000 -0.2894 0.00879 0.00249 -0.0353 0.6953 0.3559
-3.750 -0.2617 0.00854 0.00235 -0.0355 0.6889 0.3949
-3.500 -0.2338 0.00835 0.00224 -0.0357 0.6828 0.4299
-3.250 -0.2057 0.00818 0.00216 -0.0358 0.6768 0.4644
-2.500 -0.1197 0.00798 0.00200 -0.0364 0.6586 0.5169
-2.250 -0.0909 0.00795 0.00197 -0.0366 0.6523 0.5304
-2.000 -0.0620 0.00794 0.00193 -0.0368 0.6466 0.5413
-1.750 -0.0329 0.00791 0.00189 -0.0370 0.6406 0.5489
-1.500 -0.0038 0.00791 0.00186 -0.0372 0.6348 0.5559
-1.250 0.0251 0.00789 0.00184 -0.0374 0.6292 0.5625
-1.000 0.0542 0.00789 0.00182 -0.0377 0.6230 0.5695
-0.750 0.0832 0.00789 0.00180 -0.0379 0.6173 0.5757
-0.500 0.1122 0.00789 0.00180 -0.0381 0.6121 0.5822
0.000 0.1702 0.00792 0.00181 -0.0385 0.6004 0.5941
0.250 0.1993 0.00793 0.00183 -0.0388 0.5951 0.6002
0.500 0.2284 0.00795 0.00184 -0.0390 0.5892 0.6059
0.750 0.2572 0.00798 0.00187 -0.0392 0.5835 0.6118
1.000 0.2863 0.00800 0.00191 -0.0394 0.5778 0.6181
1.250 0.3152 0.00803 0.00194 -0.0396 0.5714 0.6235
1.500 0.3439 0.00807 0.00199 -0.0398 0.5655 0.6295
1.750 0.3729 0.00810 0.00205 -0.0400 0.5590 0.6361
2.000 0.4016 0.00815 0.00211 -0.0402 0.5527 0.6419
2.250 0.4304 0.00820 0.00218 -0.0404 0.5466 0.6480
2.500 0.4592 0.00825 0.00225 -0.0406 0.5397 0.6543
2.750 0.4876 0.00831 0.00233 -0.0407 0.5324 0.6604
3.000 0.5160 0.00838 0.00241 -0.0408 0.5210 0.6671
3.250 0.5443 0.00846 0.00250 -0.0409 0.5090 0.6732
3.500 0.5723 0.00854 0.00260 -0.0410 0.4990 0.6795
3.750 0.6002 0.00866 0.00271 -0.0410 0.4858 0.6864
4.000 0.6276 0.00878 0.00282 -0.0410 0.4669 0.6927
4.250 0.6544 0.00897 0.00296 -0.0409 0.4410 0.6994
4.750 0.7055 0.00958 0.00334 -0.0404 0.3706 0.7127
5.000 0.7302 0.00998 0.00361 -0.0401 0.3313 0.7198
5.250 0.7532 0.01053 0.00396 -0.0396 0.2837 0.7263
5.500 0.7752 0.01117 0.00439 -0.0390 0.2331 0.7334
5.750 0.7973 0.01178 0.00481 -0.0383 0.1896 0.7406
6.000 0.8196 0.01233 0.00524 -0.0377 0.1566 0.7476
6.250 0.8420 0.01286 0.00566 -0.0371 0.1281 0.7550
6.500 0.8639 0.01339 0.00609 -0.0364 0.1023 0.7621
6.750 0.8855 0.01392 0.00654 -0.0357 0.0810 0.7701
7.000 0.9068 0.01443 0.00700 -0.0349 0.0653 0.7774
7.250 0.9282 0.01491 0.00744 -0.0342 0.0541 0.7858
7.500 0.9492 0.01538 0.00790 -0.0333 0.0461 0.7938
7.750 0.9706 0.01579 0.00835 -0.0325 0.0413 0.8025
8.000 0.9909 0.01622 0.00882 -0.0315 0.0381 0.8112
8.250 1.0114 0.01663 0.00928 -0.0305 0.0358 0.8208
8.500 1.0299 0.01709 0.00979 -0.0293 0.0334 0.8305
8.750 1.0475 0.01757 0.01033 -0.0279 0.0317 0.8414
9.000 1.0638 0.01799 0.01082 -0.0263 0.0302 0.8535
9.250 1.0763 0.01845 0.01136 -0.0240 0.0287 0.8676
9.500 1.0867 0.01900 0.01198 -0.0215 0.0274 0.8854
9.750 1.0954 0.01957 0.01266 -0.0189 0.0264 0.9106
10.000 1.1105 0.02011 0.01333 -0.0175 0.0253 0.9599
10.250 1.1260 0.02083 0.01410 -0.0166 0.0241 1.0000
10.500 1.1395 0.02166 0.01496 -0.0154 0.0232 1.0000
10.750 1.1512 0.02264 0.01596 -0.0143 0.0223 1.0000
11.000 1.1634 0.02363 0.01699 -0.0132 0.0215 1.0000
11.250 1.1760 0.02462 0.01805 -0.0122 0.0207 1.0000
11.500 1.1882 0.02567 0.01915 -0.0113 0.0199 1.0000
11.750 1.1992 0.02684 0.02036 -0.0104 0.0192 1.0000
12.000 1.2095 0.02811 0.02166 -0.0096 0.0185 1.0000
12.250 1.2173 0.02962 0.02321 -0.0087 0.0180 1.0000
12.500 1.2273 0.03098 0.02465 -0.0080 0.0175 1.0000
12.750 1.2360 0.03250 0.02624 -0.0074 0.0171 1.0000
13.000 1.2445 0.03407 0.02788 -0.0068 0.0166 1.0000
13.250 1.2525 0.03572 0.02959 -0.0063 0.0162 1.0000
13.500 1.2603 0.03743 0.03136 -0.0059 0.0158 1.0000
13.750 1.2664 0.03934 0.03333 -0.0056 0.0154 1.0000
14.000 1.2722 0.04133 0.03538 -0.0054 0.0151 1.0000
14.250 1.2760 0.04357 0.03768 -0.0053 0.0148 1.0000
14.500 1.2797 0.04589 0.04006 -0.0052 0.0145 1.0000
14.750 1.2838 0.04824 0.04251 -0.0053 0.0143 1.0000
15.000 1.2877 0.05071 0.04508 -0.0055 0.0141 1.0000
15.250 1.2901 0.05339 0.04785 -0.0058 0.0139 1.0000
15.500 1.2932 0.05610 0.05065 -0.0063 0.0137 1.0000
15.750 1.2947 0.05907 0.05371 -0.0069 0.0136 1.0000
16.000 1.2964 0.06209 0.05684 -0.0076 0.0134 1.0000
16.250 1.2970 0.06534 0.06018 -0.0085 0.0132 1.0000
16.500 1.2969 0.06877 0.06370 -0.0096 0.0130 1.0000
16.750 1.2967 0.07232 0.06735 -0.0108 0.0129 1.0000
17.000 1.2957 0.07606 0.07118 -0.0122 0.0128 1.0000
17.250 1.2938 0.08000 0.07523 -0.0137 0.0126 1.0000
17.500 1.2912 0.08418 0.07950 -0.0154 0.0125 1.0000
17.750 1.2879 0.08856 0.08398 -0.0173 0.0124 1.0000
18.000 1.2836 0.09318 0.08871 -0.0194 0.0123 1.0000
18.250 1.2785 0.09802 0.09365 -0.0217 0.0122 1.0000
18.500 1.2723 0.10319 0.09891 -0.0243 0.0121 1.0000
18.750 1.2656 0.10853 0.10436 -0.0270 0.0120 1.0000
19.000 1.2583 0.11406 0.11000 -0.0300 0.0119 1.0000
19.250 1.2501 0.11980 0.11584 -0.0331 0.0118 1.0000
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