NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 500,000 Max Cl/Cd: 84.98 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a210-il-500000.txt Download as CSV file: xf-naca64a210-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A210
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5604 0.08453 0.08230 -0.0291 1.0000 0.0209
-9.500 -0.5680 0.07547 0.07320 -0.0379 1.0000 0.0209
-9.250 -0.5814 0.06925 0.06691 -0.0438 1.0000 0.0209
-9.000 -0.5962 0.06477 0.06232 -0.0459 1.0000 0.0209
-8.750 -0.6051 0.06032 0.05771 -0.0468 1.0000 0.0209
-8.500 -0.6112 0.05619 0.05339 -0.0466 1.0000 0.0210
-8.250 -0.6404 0.04763 0.04463 -0.0450 1.0000 0.0217
-8.000 -0.6396 0.04523 0.04217 -0.0428 1.0000 0.0221
-7.750 -0.6390 0.04342 0.04031 -0.0399 1.0000 0.0225
-7.500 -0.6393 0.04169 0.03849 -0.0366 1.0000 0.0229
-7.250 -0.6182 0.03885 0.03547 -0.0380 0.9977 0.0239
-7.000 -0.5906 0.03534 0.03164 -0.0401 0.9949 0.0258
-6.750 -0.5706 0.02577 0.02103 -0.0397 0.9903 0.0199
-6.500 -0.5426 0.02172 0.01646 -0.0405 0.9872 0.0194
-6.250 -0.5101 0.01934 0.01375 -0.0418 0.9850 0.0197
-6.000 -0.4756 0.01773 0.01190 -0.0435 0.9834 0.0203
-5.750 -0.4450 0.01642 0.01039 -0.0442 0.9796 0.0214
-5.500 -0.4143 0.01451 0.00837 -0.0453 0.9765 0.0226
-5.250 -0.3806 0.01358 0.00739 -0.0468 0.9738 0.0237
-5.000 -0.3464 0.01281 0.00658 -0.0483 0.9712 0.0251
-4.750 -0.3165 0.01218 0.00590 -0.0489 0.9664 0.0267
-4.500 -0.2862 0.01179 0.00545 -0.0495 0.9609 0.0284
-4.250 -0.2574 0.01081 0.00440 -0.0499 0.9563 0.0313
-4.000 -0.2316 0.01038 0.00395 -0.0495 0.9486 0.0347
-3.750 -0.2035 0.01003 0.00354 -0.0495 0.9427 0.0392
-3.500 -0.1785 0.00955 0.00307 -0.0490 0.9349 0.0540
-3.250 -0.1539 0.00888 0.00268 -0.0485 0.9279 0.1220
-3.000 -0.1338 0.00771 0.00230 -0.0477 0.9190 0.3313
-2.750 -0.1123 0.00690 0.00214 -0.0467 0.9118 0.5208
-2.500 -0.0877 0.00667 0.00208 -0.0460 0.9030 0.5846
-2.250 -0.0618 0.00654 0.00202 -0.0454 0.8958 0.6256
-2.000 -0.0358 0.00645 0.00197 -0.0449 0.8872 0.6546
-1.750 -0.0093 0.00640 0.00193 -0.0445 0.8793 0.6784
-1.500 0.0168 0.00635 0.00190 -0.0439 0.8711 0.7048
-1.250 0.0424 0.00632 0.00193 -0.0433 0.8623 0.7358
-0.750 0.0957 0.00626 0.00187 -0.0424 0.8450 0.7683
-0.500 0.1228 0.00624 0.00183 -0.0422 0.8365 0.7804
-0.250 0.1498 0.00619 0.00179 -0.0419 0.8274 0.7913
0.000 0.1768 0.00615 0.00177 -0.0417 0.8177 0.8027
0.250 0.2038 0.00612 0.00174 -0.0414 0.8089 0.8146
0.500 0.2306 0.00609 0.00173 -0.0411 0.7993 0.8277
0.750 0.2573 0.00605 0.00174 -0.0408 0.7894 0.8420
1.000 0.2839 0.00603 0.00175 -0.0404 0.7802 0.8579
1.250 0.3102 0.00602 0.00178 -0.0400 0.7704 0.8768
1.500 0.3366 0.00600 0.00183 -0.0395 0.7599 0.8992
1.750 0.3643 0.00602 0.00188 -0.0392 0.7477 0.9248
2.000 0.3967 0.00606 0.00193 -0.0401 0.7327 0.9483
2.250 0.4314 0.00613 0.00194 -0.0414 0.7110 0.9688
2.500 0.4680 0.00622 0.00195 -0.0433 0.6814 0.9839
2.750 0.5064 0.00634 0.00200 -0.0457 0.6548 0.9949
3.000 0.5398 0.00645 0.00206 -0.0471 0.6293 1.0000
3.250 0.5632 0.00663 0.00214 -0.0463 0.5983 1.0000
3.500 0.5855 0.00689 0.00223 -0.0453 0.5524 1.0000
3.750 0.6066 0.00728 0.00239 -0.0441 0.4871 1.0000
4.000 0.6205 0.00839 0.00276 -0.0418 0.3254 1.0000
4.250 0.6341 0.00975 0.00334 -0.0399 0.1601 1.0000
4.500 0.6524 0.01071 0.00385 -0.0385 0.0715 1.0000
4.750 0.6744 0.01133 0.00434 -0.0376 0.0439 1.0000
5.000 0.6970 0.01190 0.00490 -0.0367 0.0344 1.0000
5.250 0.7194 0.01251 0.00550 -0.0358 0.0293 1.0000
5.500 0.7416 0.01313 0.00619 -0.0348 0.0267 1.0000
5.750 0.7645 0.01368 0.00678 -0.0340 0.0250 1.0000
6.000 0.7869 0.01429 0.00745 -0.0331 0.0235 1.0000
6.250 0.8086 0.01499 0.00817 -0.0322 0.0223 1.0000
6.500 0.8284 0.01603 0.00926 -0.0309 0.0212 1.0000
6.750 0.8453 0.01804 0.01136 -0.0292 0.0202 1.0000
7.000 0.8696 0.01849 0.01190 -0.0287 0.0196 1.0000
7.250 0.8926 0.01938 0.01289 -0.0279 0.0189 1.0000
7.500 0.9154 0.02061 0.01422 -0.0271 0.0184 1.0000
7.750 0.9380 0.02201 0.01576 -0.0263 0.0179 1.0000
8.000 0.9602 0.02364 0.01755 -0.0255 0.0175 1.0000
8.250 0.9813 0.02554 0.01967 -0.0245 0.0171 1.0000
8.500 1.0018 0.02693 0.02121 -0.0236 0.0165 1.0000
8.750 1.0213 0.02791 0.02226 -0.0228 0.0157 1.0000
9.000 1.0374 0.03023 0.02475 -0.0216 0.0152 1.0000
9.250 1.0495 0.03349 0.02833 -0.0198 0.0150 1.0000
9.500 1.0591 0.03665 0.03183 -0.0177 0.0151 1.0000
12.250 0.6572 0.11474 0.11266 -0.0159 0.0255 1.0000
12.500 0.6463 0.12072 0.11863 -0.0184 0.0249 1.0000
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Polar data table (+)
Polar graphs
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