NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-210 (naca65210-il) Reynolds number: 200,000 Max Cl/Cd: 50.83 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65210-il-200000-n5.txt Download as CSV file: xf-naca65210-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5519 0.08626 0.08270 -0.0304 1.0000 0.0147
-9.750 -0.5674 0.07668 0.07318 -0.0376 1.0000 0.0140
-9.500 -0.6009 0.06505 0.06146 -0.0463 1.0000 0.0134
-9.250 -0.6222 0.05981 0.05611 -0.0473 1.0000 0.0133
-9.000 -0.6379 0.05505 0.05116 -0.0465 1.0000 0.0131
-8.750 -0.6468 0.05122 0.04717 -0.0455 1.0000 0.0132
-8.500 -0.6511 0.04771 0.04346 -0.0442 1.0000 0.0134
-8.250 -0.6513 0.04462 0.04017 -0.0425 1.0000 0.0136
-8.000 -0.6423 0.04378 0.03928 -0.0412 1.0000 0.0142
-7.750 -0.6383 0.04156 0.03689 -0.0391 1.0000 0.0148
-7.500 -0.6347 0.03943 0.03457 -0.0364 1.0000 0.0157
-7.250 -0.6136 0.03480 0.02942 -0.0376 0.9926 0.0165
-7.000 -0.5881 0.03053 0.02455 -0.0389 0.9861 0.0170
-6.750 -0.5608 0.02725 0.02070 -0.0397 0.9797 0.0179
-6.500 -0.5302 0.02488 0.01784 -0.0409 0.9750 0.0192
-6.250 -0.5023 0.02314 0.01598 -0.0420 0.9683 0.0207
-6.000 -0.4702 0.02160 0.01421 -0.0434 0.9639 0.0218
-5.750 -0.4412 0.02023 0.01264 -0.0439 0.9568 0.0229
-5.500 -0.4093 0.01901 0.01122 -0.0449 0.9517 0.0243
-5.250 -0.3801 0.01823 0.01030 -0.0454 0.9445 0.0264
-5.000 -0.3498 0.01731 0.00926 -0.0460 0.9384 0.0273
-4.750 -0.3235 0.01609 0.00798 -0.0460 0.9308 0.0285
-4.500 -0.2969 0.01510 0.00694 -0.0461 0.9238 0.0303
-4.250 -0.2714 0.01447 0.00627 -0.0459 0.9155 0.0324
-4.000 -0.2440 0.01399 0.00572 -0.0460 0.9087 0.0360
-3.750 -0.2186 0.01356 0.00520 -0.0457 0.9002 0.0387
-3.250 -0.1668 0.01266 0.00415 -0.0452 0.8854 0.0500
-3.000 -0.1410 0.01218 0.00375 -0.0450 0.8789 0.0752
-2.750 -0.1207 0.01085 0.00328 -0.0446 0.8704 0.2868
-2.500 -0.1026 0.00960 0.00319 -0.0433 0.8636 0.5800
-2.250 -0.0802 0.00946 0.00338 -0.0418 0.8561 0.6816
-2.000 -0.0554 0.00949 0.00346 -0.0407 0.8501 0.7240
-1.750 -0.0302 0.00954 0.00351 -0.0398 0.8426 0.7483
-1.500 -0.0039 0.00956 0.00347 -0.0392 0.8370 0.7654
-1.250 0.0227 0.00956 0.00344 -0.0389 0.8300 0.7730
-1.000 0.0504 0.00954 0.00335 -0.0389 0.8239 0.7804
-0.750 0.0774 0.00953 0.00332 -0.0386 0.8174 0.7863
-0.500 0.1049 0.00953 0.00326 -0.0386 0.8113 0.7937
-0.250 0.1320 0.00953 0.00325 -0.0384 0.8056 0.7996
0.000 0.1593 0.00954 0.00324 -0.0383 0.7989 0.8067
0.250 0.1865 0.00955 0.00324 -0.0381 0.7937 0.8130
0.500 0.2135 0.00957 0.00328 -0.0380 0.7869 0.8202
0.750 0.2406 0.00958 0.00330 -0.0378 0.7811 0.8267
1.000 0.2676 0.00961 0.00336 -0.0376 0.7751 0.8340
1.250 0.2944 0.00964 0.00343 -0.0374 0.7688 0.8411
1.500 0.3213 0.00968 0.00350 -0.0371 0.7633 0.8484
1.750 0.3478 0.00972 0.00360 -0.0368 0.7564 0.8556
2.000 0.3745 0.00976 0.00370 -0.0365 0.7509 0.8635
2.250 0.4004 0.00980 0.00384 -0.0361 0.7430 0.8711
2.500 0.4261 0.00980 0.00387 -0.0355 0.7300 0.8797
2.750 0.4498 0.00974 0.00379 -0.0341 0.7053 0.8876
3.000 0.4728 0.00971 0.00372 -0.0327 0.6680 0.8969
3.250 0.4941 0.00980 0.00362 -0.0309 0.6068 0.9069
3.500 0.5139 0.01011 0.00361 -0.0291 0.5123 0.9172
3.750 0.5223 0.01156 0.00399 -0.0260 0.2874 0.9314
4.000 0.5364 0.01307 0.00465 -0.0245 0.1054 0.9465
4.250 0.5613 0.01389 0.00523 -0.0245 0.0529 0.9605
4.500 0.5918 0.01445 0.00579 -0.0255 0.0417 0.9751
4.750 0.6226 0.01505 0.00644 -0.0267 0.0363 1.0000
5.000 0.6436 0.01580 0.00723 -0.0259 0.0328 1.0000
5.250 0.6667 0.01634 0.00787 -0.0254 0.0300 1.0000
5.500 0.6889 0.01703 0.00861 -0.0247 0.0278 1.0000
5.750 0.7105 0.01783 0.00945 -0.0240 0.0262 1.0000
6.000 0.7317 0.01877 0.01041 -0.0232 0.0249 1.0000
6.250 0.7522 0.02012 0.01179 -0.0224 0.0237 1.0000
6.500 0.7749 0.02172 0.01347 -0.0217 0.0229 1.0000
6.750 0.7994 0.02283 0.01470 -0.0213 0.0224 1.0000
7.000 0.8239 0.02384 0.01587 -0.0210 0.0212 1.0000
7.250 0.8480 0.02509 0.01728 -0.0206 0.0201 1.0000
7.500 0.8717 0.02671 0.01911 -0.0201 0.0193 1.0000
7.750 0.8943 0.02850 0.02114 -0.0195 0.0187 1.0000
8.000 0.9153 0.03043 0.02334 -0.0187 0.0180 1.0000
8.250 0.9345 0.03212 0.02525 -0.0179 0.0173 1.0000
8.500 0.9522 0.03350 0.02674 -0.0172 0.0163 1.0000
8.750 0.9639 0.03664 0.03021 -0.0159 0.0154 1.0000
9.000 0.9746 0.03948 0.03349 -0.0140 0.0151 1.0000
9.250 0.9803 0.04295 0.03743 -0.0118 0.0147 1.0000
9.500 0.9802 0.04687 0.04177 -0.0093 0.0144 1.0000
9.750 0.9750 0.05092 0.04619 -0.0067 0.0143 1.0000
10.000 0.9629 0.05491 0.05050 -0.0037 0.0141 1.0000
10.250 0.9468 0.05857 0.05439 -0.0009 0.0140 1.0000
10.500 0.9290 0.06247 0.05850 0.0008 0.0139 1.0000
10.750 0.9087 0.06704 0.06325 0.0011 0.0139 1.0000
11.000 0.8874 0.07227 0.06865 -0.0001 0.0140 1.0000
11.250 0.8658 0.07834 0.07485 -0.0029 0.0142 1.0000
11.500 0.8435 0.08582 0.08245 -0.0076 0.0144 1.0000
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Polar data table (+)
Polar graphs
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