NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-215 AIRFOIL (n63215-il) Reynolds number: 500,000 Max Cl/Cd: 85.73 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63215-il-500000.txt Download as CSV file: xf-n63215-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9226 0.09045 0.08723 -0.0342 1.0000 0.0189
-16.500 -0.9440 0.08271 0.07932 -0.0391 1.0000 0.0189
-16.250 -0.9610 0.07621 0.07267 -0.0430 1.0000 0.0190
-16.000 -0.9735 0.07079 0.06710 -0.0460 1.0000 0.0191
-15.750 -0.9958 0.06421 0.06027 -0.0492 1.0000 0.0190
-15.500 -0.9977 0.06095 0.05695 -0.0508 1.0000 0.0193
-15.250 -1.0043 0.05720 0.05307 -0.0523 1.0000 0.0195
-15.000 -1.0100 0.05370 0.04942 -0.0536 1.0000 0.0197
-14.750 -1.0128 0.05070 0.04631 -0.0545 1.0000 0.0200
-14.500 -1.0173 0.04748 0.04293 -0.0551 1.0000 0.0202
-14.250 -1.0185 0.04477 0.04008 -0.0554 1.0000 0.0204
-14.000 -1.0185 0.04227 0.03744 -0.0555 1.0000 0.0207
-13.750 -1.0170 0.03994 0.03495 -0.0554 1.0000 0.0209
-13.500 -1.0141 0.03790 0.03276 -0.0552 1.0000 0.0213
-13.250 -1.0100 0.03604 0.03075 -0.0547 1.0000 0.0216
-13.000 -1.0046 0.03424 0.02880 -0.0541 1.0000 0.0218
-12.750 -0.9946 0.03222 0.02672 -0.0533 1.0000 0.0224
-12.500 -0.9840 0.03090 0.02538 -0.0526 1.0000 0.0228
-12.250 -0.9734 0.02980 0.02426 -0.0520 1.0000 0.0233
-12.000 -0.9626 0.02868 0.02309 -0.0513 1.0000 0.0239
-11.750 -0.9509 0.02753 0.02187 -0.0504 1.0000 0.0245
-11.500 -0.9386 0.02647 0.02074 -0.0494 1.0000 0.0250
-11.250 -0.9259 0.02548 0.01965 -0.0484 1.0000 0.0256
-11.000 -0.9133 0.02464 0.01872 -0.0472 1.0000 0.0261
-10.750 -0.9014 0.02325 0.01729 -0.0458 1.0000 0.0267
-10.500 -0.8916 0.02218 0.01623 -0.0442 1.0000 0.0274
-10.250 -0.8817 0.02144 0.01549 -0.0423 1.0000 0.0281
-10.000 -0.8696 0.02081 0.01485 -0.0406 1.0000 0.0289
-9.750 -0.8420 0.02008 0.01406 -0.0418 0.9856 0.0302
-9.500 -0.8046 0.01939 0.01327 -0.0446 0.9704 0.0314
-9.250 -0.7768 0.01798 0.01185 -0.0464 0.9516 0.0332
-9.000 -0.7539 0.01739 0.01120 -0.0462 0.9323 0.0346
-8.750 -0.7351 0.01691 0.01063 -0.0450 0.9157 0.0360
-8.500 -0.7150 0.01656 0.01017 -0.0439 0.9020 0.0373
-8.250 -0.7002 0.01573 0.00928 -0.0422 0.8893 0.0394
-8.000 -0.6798 0.01529 0.00878 -0.0413 0.8784 0.0415
-7.750 -0.6576 0.01489 0.00832 -0.0406 0.8682 0.0436
-7.500 -0.6367 0.01438 0.00772 -0.0396 0.8591 0.0459
-7.250 -0.6147 0.01386 0.00719 -0.0390 0.8497 0.0489
-7.000 -0.5907 0.01354 0.00679 -0.0385 0.8417 0.0521
-6.750 -0.5675 0.01303 0.00626 -0.0380 0.8330 0.0569
-6.500 -0.5429 0.01269 0.00587 -0.0376 0.8256 0.0625
-6.250 -0.5188 0.01219 0.00541 -0.0373 0.8174 0.0741
-6.000 -0.4956 0.01160 0.00493 -0.0369 0.8103 0.1018
-5.750 -0.4725 0.01086 0.00446 -0.0366 0.8023 0.1563
-5.500 -0.4496 0.01010 0.00399 -0.0364 0.7954 0.2256
-5.250 -0.4259 0.00932 0.00357 -0.0363 0.7880 0.3100
-5.000 -0.4010 0.00876 0.00329 -0.0362 0.7810 0.3848
-4.750 -0.3739 0.00852 0.00314 -0.0362 0.7744 0.4279
-4.500 -0.3459 0.00838 0.00303 -0.0363 0.7673 0.4557
-4.250 -0.3180 0.00829 0.00293 -0.0363 0.7610 0.4769
-4.000 -0.2894 0.00820 0.00285 -0.0365 0.7539 0.4947
-3.750 -0.2609 0.00816 0.00277 -0.0366 0.7474 0.5089
-3.500 -0.2323 0.00813 0.00271 -0.0367 0.7412 0.5236
-3.250 -0.2037 0.00810 0.00269 -0.0368 0.7342 0.5410
-3.000 -0.1752 0.00812 0.00265 -0.0369 0.7281 0.5553
-2.750 -0.1463 0.00809 0.00264 -0.0371 0.7214 0.5660
-2.500 -0.1175 0.00806 0.00259 -0.0372 0.7150 0.5747
-2.250 -0.0887 0.00811 0.00256 -0.0373 0.7090 0.5855
-2.000 -0.0599 0.00806 0.00256 -0.0375 0.7021 0.5941
-1.750 -0.0308 0.00809 0.00250 -0.0377 0.6962 0.6016
-1.500 -0.0020 0.00805 0.00249 -0.0378 0.6901 0.6080
-1.250 0.0271 0.00805 0.00247 -0.0380 0.6836 0.6149
-1.000 0.0560 0.00808 0.00243 -0.0382 0.6778 0.6216
-0.750 0.0850 0.00805 0.00244 -0.0384 0.6714 0.6279
-0.500 0.1141 0.00807 0.00242 -0.0387 0.6654 0.6349
-0.250 0.1429 0.00808 0.00243 -0.0388 0.6596 0.6408
0.000 0.1720 0.00807 0.00244 -0.0390 0.6531 0.6473
0.250 0.2010 0.00811 0.00243 -0.0392 0.6474 0.6538
0.500 0.2298 0.00811 0.00248 -0.0394 0.6414 0.6596
0.750 0.2589 0.00813 0.00250 -0.0396 0.6351 0.6664
1.000 0.2877 0.00818 0.00252 -0.0398 0.6294 0.6726
1.250 0.3166 0.00819 0.00258 -0.0400 0.6230 0.6788
1.500 0.3456 0.00823 0.00260 -0.0402 0.6166 0.6857
1.750 0.3741 0.00827 0.00267 -0.0403 0.6107 0.6917
2.000 0.4030 0.00829 0.00273 -0.0405 0.6041 0.6987
2.250 0.4317 0.00835 0.00278 -0.0406 0.5980 0.7051
2.500 0.4603 0.00838 0.00287 -0.0408 0.5915 0.7115
2.750 0.4891 0.00843 0.00292 -0.0409 0.5843 0.7188
3.000 0.5172 0.00846 0.00300 -0.0410 0.5757 0.7251
3.250 0.5455 0.00851 0.00305 -0.0410 0.5663 0.7321
3.500 0.5739 0.00856 0.00314 -0.0411 0.5580 0.7389
3.750 0.6017 0.00862 0.00322 -0.0411 0.5488 0.7457
4.250 0.6572 0.00871 0.00338 -0.0410 0.5228 0.7598
4.500 0.6847 0.00880 0.00347 -0.0409 0.5064 0.7673
4.750 0.7119 0.00889 0.00359 -0.0408 0.4932 0.7742
5.000 0.7391 0.00900 0.00372 -0.0407 0.4792 0.7819
5.250 0.7660 0.00914 0.00386 -0.0406 0.4617 0.7891
5.500 0.7921 0.00931 0.00403 -0.0403 0.4407 0.7967
5.750 0.8179 0.00954 0.00422 -0.0400 0.4149 0.8046
6.000 0.8416 0.00988 0.00447 -0.0394 0.3772 0.8123
6.250 0.8627 0.01049 0.00484 -0.0386 0.3206 0.8208
6.500 0.8807 0.01130 0.00537 -0.0373 0.2560 0.8293
6.750 0.8981 0.01218 0.00596 -0.0360 0.1959 0.8383
7.000 0.9148 0.01304 0.00658 -0.0346 0.1456 0.8480
7.250 0.9309 0.01385 0.00719 -0.0331 0.1042 0.8578
7.500 0.9470 0.01464 0.00781 -0.0315 0.0761 0.8690
7.750 0.9639 0.01522 0.00838 -0.0299 0.0625 0.8807
8.000 0.9790 0.01581 0.00897 -0.0279 0.0547 0.8940
8.250 0.9948 0.01623 0.00946 -0.0260 0.0504 0.9101
8.500 1.0039 0.01681 0.01009 -0.0230 0.0466 0.9336
8.750 1.0254 0.01720 0.01059 -0.0224 0.0439 0.9827
9.000 1.0421 0.01782 0.01121 -0.0213 0.0412 1.0000
9.250 1.0515 0.01879 0.01217 -0.0192 0.0388 1.0000
9.500 1.0676 0.01941 0.01285 -0.0181 0.0371 1.0000
9.750 1.0815 0.02018 0.01364 -0.0168 0.0352 1.0000
10.000 1.0907 0.02125 0.01471 -0.0152 0.0335 1.0000
10.250 1.0973 0.02255 0.01606 -0.0134 0.0321 1.0000
10.500 1.1104 0.02349 0.01706 -0.0123 0.0309 1.0000
10.750 1.1221 0.02456 0.01817 -0.0113 0.0297 1.0000
11.000 1.1322 0.02576 0.01939 -0.0102 0.0286 1.0000
11.250 1.1372 0.02740 0.02104 -0.0089 0.0276 1.0000
11.500 1.1447 0.02894 0.02266 -0.0078 0.0266 1.0000
11.750 1.1558 0.03022 0.02402 -0.0070 0.0258 1.0000
12.000 1.1660 0.03160 0.02546 -0.0063 0.0251 1.0000
12.250 1.1757 0.03306 0.02695 -0.0057 0.0243 1.0000
12.500 1.1843 0.03463 0.02856 -0.0050 0.0237 1.0000
12.750 1.1908 0.03644 0.03040 -0.0044 0.0231 1.0000
13.000 1.1939 0.03867 0.03266 -0.0034 0.0224 1.0000
13.250 1.2034 0.04028 0.03437 -0.0030 0.0221 1.0000
13.500 1.2119 0.04203 0.03622 -0.0027 0.0216 1.0000
13.750 1.2198 0.04387 0.03814 -0.0024 0.0212 1.0000
14.000 1.2271 0.04581 0.04017 -0.0021 0.0209 1.0000
14.250 1.2337 0.04784 0.04229 -0.0019 0.0205 1.0000
14.500 1.2401 0.04995 0.04448 -0.0019 0.0201 1.0000
14.750 1.2460 0.05215 0.04674 -0.0020 0.0197 1.0000
15.000 1.2515 0.05446 0.04911 -0.0021 0.0194 1.0000
15.250 1.2567 0.05682 0.05150 -0.0023 0.0191 1.0000
15.500 1.2613 0.05937 0.05411 -0.0024 0.0187 1.0000
15.750 1.2627 0.06241 0.05728 -0.0026 0.0184 1.0000
16.000 1.2638 0.06551 0.06052 -0.0034 0.0182 1.0000
16.250 1.2632 0.06894 0.06410 -0.0043 0.0180 1.0000
16.500 1.2616 0.07259 0.06790 -0.0054 0.0179 1.0000
16.750 1.2591 0.07649 0.07196 -0.0067 0.0177 1.0000
17.000 1.2545 0.08082 0.07645 -0.0083 0.0175 1.0000
17.250 1.2490 0.08540 0.08118 -0.0102 0.0174 1.0000
17.500 1.2416 0.09040 0.08634 -0.0125 0.0172 1.0000
17.750 1.2325 0.09589 0.09201 -0.0151 0.0171 1.0000
18.000 1.2211 0.10195 0.09823 -0.0182 0.0170 1.0000
18.250 1.2085 0.10843 0.10489 -0.0217 0.0169 1.0000
18.500 1.1913 0.11603 0.11268 -0.0261 0.0169 1.0000
18.750 1.1727 0.12424 0.12109 -0.0311 0.0169 1.0000
19.000 1.1439 0.13509 0.13218 -0.0381 0.0170 1.0000
19.250 1.1016 0.14999 0.14737 -0.0480 0.0172 1.0000
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