NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-210 AIRFOIL (n63210-il) Reynolds number: 500,000 Max Cl/Cd: 55.8 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63210-il-500000-n5.txt Download as CSV file: xf-n63210-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-210 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.9148 0.04026 0.03732 -0.0458 1.0000 0.0052
-11.250 -0.9486 0.03396 0.03050 -0.0435 1.0000 0.0053
-11.000 -0.9533 0.02981 0.02590 -0.0421 1.0000 0.0054
-10.750 -0.9461 0.02697 0.02270 -0.0410 1.0000 0.0056
-10.500 -0.9347 0.02454 0.01992 -0.0400 1.0000 0.0058
-10.250 -0.9190 0.02272 0.01784 -0.0392 1.0000 0.0060
-10.000 -0.8998 0.02151 0.01646 -0.0386 1.0000 0.0063
-9.750 -0.8770 0.02101 0.01592 -0.0382 1.0000 0.0067
-9.500 -0.8525 0.02089 0.01582 -0.0380 1.0000 0.0071
-9.250 -0.8264 0.02121 0.01620 -0.0380 1.0000 0.0075
-9.000 -0.8024 0.02106 0.01603 -0.0377 1.0000 0.0080
-8.750 -0.7800 0.02047 0.01535 -0.0373 1.0000 0.0086
-8.500 -0.7591 0.01927 0.01392 -0.0364 1.0000 0.0112
-8.250 -0.7356 0.01898 0.01347 -0.0358 1.0000 0.0123
-8.000 -0.7148 0.01822 0.01261 -0.0350 1.0000 0.0130
-7.750 -0.6864 0.01773 0.01211 -0.0358 0.9962 0.0139
-7.500 -0.6540 0.01735 0.01166 -0.0373 0.9901 0.0149
-7.250 -0.6209 0.01691 0.01114 -0.0389 0.9845 0.0159
-7.000 -0.5888 0.01650 0.01066 -0.0402 0.9776 0.0170
-6.750 -0.5569 0.01614 0.01021 -0.0414 0.9699 0.0178
-6.500 -0.5253 0.01588 0.00987 -0.0424 0.9614 0.0183
-6.250 -0.4979 0.01492 0.00879 -0.0427 0.9501 0.0189
-6.000 -0.4729 0.01396 0.00773 -0.0425 0.9353 0.0197
-5.750 -0.4481 0.01334 0.00704 -0.0421 0.9151 0.0204
-5.250 -0.3989 0.01239 0.00587 -0.0409 0.8781 0.0204
-4.750 -0.3477 0.01163 0.00488 -0.0402 0.8558 0.0202
-4.500 -0.3213 0.01129 0.00447 -0.0400 0.8467 0.0201
-4.250 -0.2947 0.01099 0.00408 -0.0399 0.8380 0.0200
-4.000 -0.2675 0.01069 0.00372 -0.0398 0.8292 0.0200
-3.750 -0.2404 0.01043 0.00340 -0.0398 0.8209 0.0200
-3.500 -0.2130 0.01019 0.00310 -0.0398 0.8118 0.0199
-3.250 -0.1854 0.00997 0.00283 -0.0398 0.8031 0.0200
-3.000 -0.1578 0.00979 0.00257 -0.0397 0.7943 0.0200
-2.750 -0.1300 0.00961 0.00234 -0.0398 0.7851 0.0202
-2.500 -0.1022 0.00947 0.00214 -0.0398 0.7765 0.0204
-2.250 -0.0743 0.00934 0.00196 -0.0398 0.7676 0.0207
-2.000 -0.0463 0.00923 0.00179 -0.0398 0.7588 0.0213
-1.750 -0.0184 0.00914 0.00166 -0.0398 0.7505 0.0224
-1.500 0.0098 0.00904 0.00155 -0.0399 0.7416 0.0246
-1.250 0.0358 0.00762 0.00120 -0.0407 0.7333 0.3342
-1.000 0.0630 0.00707 0.00112 -0.0410 0.7246 0.4763
-0.750 0.0908 0.00686 0.00116 -0.0411 0.7162 0.5509
-0.500 0.1190 0.00686 0.00116 -0.0412 0.7078 0.5840
-0.250 0.1473 0.00682 0.00115 -0.0413 0.6989 0.6044
0.000 0.1755 0.00679 0.00115 -0.0413 0.6906 0.6162
0.250 0.2026 0.00671 0.00116 -0.0411 0.6692 0.6450
0.500 0.2292 0.00674 0.00119 -0.0408 0.6381 0.6787
0.750 0.2570 0.00680 0.00122 -0.0408 0.6194 0.6934
1.000 0.2849 0.00687 0.00125 -0.0408 0.5993 0.7041
1.250 0.3125 0.00695 0.00130 -0.0407 0.5778 0.7146
1.500 0.3399 0.00707 0.00135 -0.0406 0.5494 0.7249
1.750 0.3669 0.00725 0.00142 -0.0405 0.5112 0.7355
2.000 0.3914 0.00779 0.00157 -0.0401 0.4102 0.7466
2.250 0.4134 0.00883 0.00194 -0.0396 0.2405 0.7577
2.500 0.4345 0.01012 0.00245 -0.0391 0.0504 0.7687
2.750 0.4609 0.01044 0.00268 -0.0389 0.0244 0.7799
3.250 0.5149 0.01078 0.00310 -0.0386 0.0207 0.8020
3.500 0.5416 0.01095 0.00334 -0.0385 0.0203 0.8128
3.750 0.5682 0.01115 0.00360 -0.0382 0.0200 0.8235
4.000 0.5945 0.01137 0.00390 -0.0380 0.0196 0.8356
4.250 0.6203 0.01161 0.00422 -0.0376 0.0192 0.8482
4.500 0.6455 0.01188 0.00456 -0.0371 0.0189 0.8600
4.750 0.6702 0.01218 0.00494 -0.0365 0.0185 0.8729
5.000 0.6941 0.01250 0.00537 -0.0357 0.0182 0.8875
5.250 0.7172 0.01286 0.00581 -0.0348 0.0179 0.9038
5.500 0.7394 0.01325 0.00629 -0.0338 0.0177 0.9221
5.750 0.7610 0.01366 0.00678 -0.0326 0.0175 0.9423
6.000 0.7859 0.01415 0.00735 -0.0322 0.0173 0.9673
6.250 0.8130 0.01475 0.00803 -0.0324 0.0172 1.0000
6.500 0.8372 0.01541 0.00874 -0.0320 0.0171 1.0000
6.750 0.8611 0.01611 0.00950 -0.0316 0.0171 1.0000
7.000 0.8845 0.01689 0.01035 -0.0311 0.0170 1.0000
7.250 0.9078 0.01770 0.01123 -0.0306 0.0170 1.0000
7.500 0.9314 0.01844 0.01206 -0.0302 0.0167 1.0000
7.750 0.9550 0.01906 0.01272 -0.0299 0.0159 1.0000
8.000 0.9778 0.01981 0.01350 -0.0295 0.0152 1.0000
8.250 0.9990 0.02095 0.01471 -0.0289 0.0146 1.0000
8.500 1.0197 0.02240 0.01628 -0.0282 0.0142 1.0000
8.750 1.0389 0.02444 0.01851 -0.0274 0.0138 1.0000
9.000 1.0620 0.02463 0.01881 -0.0270 0.0135 1.0000
9.250 1.0844 0.02499 0.01927 -0.0265 0.0131 1.0000
9.500 1.1061 0.02546 0.01984 -0.0260 0.0125 1.0000
9.750 1.1267 0.02610 0.02059 -0.0253 0.0119 1.0000
10.000 1.1462 0.02687 0.02147 -0.0246 0.0113 1.0000
10.250 1.1652 0.02753 0.02222 -0.0238 0.0107 1.0000
10.500 1.1837 0.02805 0.02282 -0.0230 0.0102 1.0000
10.750 1.2017 0.02849 0.02332 -0.0221 0.0098 1.0000
11.000 1.2188 0.02885 0.02369 -0.0211 0.0094 1.0000
11.250 1.2315 0.02974 0.02467 -0.0196 0.0091 1.0000
11.500 1.2378 0.03220 0.02755 -0.0174 0.0078 1.0000
11.750 1.2437 0.03381 0.02936 -0.0154 0.0068 1.0000
12.000 1.2548 0.03448 0.03010 -0.0140 0.0063 1.0000
12.250 1.2618 0.03572 0.03144 -0.0125 0.0061 1.0000
12.500 1.2709 0.03676 0.03257 -0.0114 0.0058 1.0000
12.750 1.2822 0.03756 0.03340 -0.0106 0.0056 1.0000
13.000 1.2930 0.03849 0.03437 -0.0100 0.0054 1.0000
13.250 1.3047 0.03940 0.03532 -0.0095 0.0051 1.0000
13.500 1.3092 0.04125 0.03725 -0.0090 0.0050 1.0000
13.750 1.3177 0.04268 0.03870 -0.0088 0.0048 1.0000
14.000 1.3198 0.04500 0.04113 -0.0087 0.0046 1.0000
14.250 1.3184 0.04786 0.04410 -0.0089 0.0044 1.0000
14.500 1.3125 0.05148 0.04788 -0.0096 0.0044 1.0000
14.750 1.3049 0.05556 0.05213 -0.0108 0.0043 1.0000
15.000 1.2940 0.06038 0.05711 -0.0126 0.0042 1.0000
15.250 1.2787 0.06626 0.06315 -0.0154 0.0041 1.0000
15.500 1.2592 0.07333 0.07044 -0.0192 0.0042 1.0000
15.750 1.2352 0.08196 0.07929 -0.0243 0.0042 1.0000
16.000 1.1886 0.09665 0.09431 -0.0336 0.0044 1.0000
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