NACA 2421 (naca2421-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2421 (naca2421-il) Reynolds number: 50,000 Max Cl/Cd: 6.86 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2421-il-50000.txt Download as CSV file: xf-naca2421-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2421
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6101 0.07993 0.07184 -0.0247 1.0000 0.2984
-8.500 -0.6835 0.07396 0.06592 -0.0189 1.0000 0.2970
-8.250 -0.7624 0.06698 0.05883 -0.0128 1.0000 0.2960
-8.000 -0.8246 0.06065 0.05220 -0.0070 1.0000 0.2972
-7.750 -0.8258 0.05864 0.05018 -0.0043 1.0000 0.3022
-7.500 -0.8101 0.05850 0.05015 -0.0023 1.0000 0.3090
-7.250 -0.8321 0.05474 0.04609 0.0013 1.0000 0.3148
-7.000 -0.8440 0.05148 0.04252 0.0041 1.0000 0.3210
-6.750 -0.8244 0.05160 0.04285 0.0057 1.0000 0.3284
-6.500 -0.8278 0.04917 0.04011 0.0080 1.0000 0.3370
-6.250 -0.8184 0.04798 0.03889 0.0097 1.0000 0.3447
-6.000 -0.8065 0.04730 0.03822 0.0114 1.0000 0.3537
-5.750 -0.8006 0.04555 0.03624 0.0129 1.0000 0.3634
-5.500 -0.7853 0.04535 0.03616 0.0144 1.0000 0.3725
-5.250 -0.7768 0.04389 0.03445 0.0155 1.0000 0.3838
-5.000 -0.7609 0.04380 0.03452 0.0170 1.0000 0.3935
-4.750 -0.7494 0.04274 0.03328 0.0179 1.0000 0.4058
-4.500 -0.7271 0.04272 0.03337 0.0180 0.9976 0.4181
-4.250 -0.6815 0.04293 0.03359 0.0138 0.9855 0.4360
-4.000 -0.6401 0.04304 0.03367 0.0103 0.9736 0.4542
-3.750 -0.5992 0.04322 0.03382 0.0070 0.9623 0.4736
-3.500 -0.5675 0.04313 0.03369 0.0052 0.9504 0.4925
-3.250 -0.5363 0.04334 0.03394 0.0040 0.9386 0.5105
-3.000 -0.4979 0.04379 0.03447 0.0019 0.9276 0.5300
-2.750 -0.4702 0.04395 0.03470 0.0014 0.9158 0.5479
-2.500 -0.4423 0.04414 0.03492 0.0009 0.9044 0.5671
-2.250 -0.4056 0.04450 0.03532 -0.0009 0.8937 0.5891
-2.000 -0.3872 0.04459 0.03542 0.0000 0.8820 0.6088
-1.750 -0.3428 0.04520 0.03611 -0.0023 0.8718 0.6341
-1.500 -0.3348 0.04527 0.03621 0.0003 0.8602 0.6541
-1.250 -0.2939 0.04594 0.03698 -0.0010 0.8502 0.6808
-1.000 -0.2862 0.04620 0.03732 0.0019 0.8387 0.7028
-0.750 -0.2458 0.04696 0.03816 0.0012 0.8293 0.7319
-0.500 -0.2411 0.04740 0.03867 0.0047 0.8180 0.7553
0.000 -0.1982 0.04871 0.04005 0.0075 0.7981 0.8151
0.250 -0.1347 0.04999 0.04135 0.0038 0.7883 0.8461
0.500 -0.1221 0.05119 0.04258 0.0052 0.7770 0.8725
0.750 -0.0262 0.05264 0.04392 -0.0049 0.7668 0.9043
1.000 0.0229 0.05453 0.04580 -0.0110 0.7530 0.9259
1.250 0.1364 0.05607 0.04726 -0.0263 0.7407 0.9467
1.500 0.2315 0.05702 0.04818 -0.0394 0.7276 0.9676
1.750 0.3055 0.05819 0.04935 -0.0501 0.7144 0.9883
2.000 0.3946 0.05753 0.04863 -0.0611 0.7042 1.0000
2.250 0.3406 0.05931 0.05038 -0.0528 0.6941 1.0000
2.500 0.3293 0.05960 0.05059 -0.0491 0.6853 1.0000
2.750 0.3283 0.05979 0.05070 -0.0463 0.6774 1.0000
3.000 0.2726 0.06115 0.05199 -0.0376 0.6688 1.0000
3.250 0.3058 0.06075 0.05149 -0.0379 0.6599 1.0000
3.500 0.2579 0.06250 0.05315 -0.0303 0.6517 1.0000
3.750 0.2599 0.06332 0.05388 -0.0277 0.6424 1.0000
4.000 0.2728 0.06424 0.05470 -0.0262 0.6335 1.0000
4.250 0.2570 0.06601 0.05640 -0.0226 0.6243 1.0000
4.500 0.3027 0.06621 0.05652 -0.0239 0.6143 1.0000
4.750 0.2711 0.06899 0.05926 -0.0198 0.6056 1.0000
5.000 0.3295 0.06872 0.05893 -0.0217 0.5947 1.0000
5.250 0.2919 0.07222 0.06239 -0.0179 0.5864 1.0000
5.500 0.3237 0.07303 0.06317 -0.0182 0.5758 1.0000
5.750 0.3152 0.07571 0.06581 -0.0165 0.5668 1.0000
6.000 0.3222 0.07778 0.06787 -0.0158 0.5580 1.0000
6.250 0.3428 0.07938 0.06944 -0.0156 0.5480 1.0000
6.500 0.3311 0.08254 0.07259 -0.0145 0.5413 1.0000
6.750 0.2204 0.09419 0.08444 -0.0161 0.6456 1.0000
7.000 0.2825 0.09328 0.08344 -0.0156 0.5797 1.0000
7.250 0.3114 0.09630 0.08645 -0.0170 0.5747 1.0000
7.500 0.3200 0.09666 0.08676 -0.0149 0.5460 1.0000
7.750 0.3480 0.09851 0.08861 -0.0153 0.5332 1.0000
8.000 0.3673 0.10188 0.09198 -0.0162 0.5298 1.0000
8.250 0.3897 0.10270 0.09276 -0.0153 0.5086 1.0000
8.500 0.4225 0.10323 0.09328 -0.0146 0.4884 1.0000
8.750 0.3176 0.11380 0.10400 -0.0172 0.5688 1.0000
9.000 0.3352 0.11607 0.10627 -0.0175 0.5555 1.0000
9.250 0.3491 0.11962 0.10982 -0.0182 0.5497 1.0000
9.500 0.3494 0.12080 0.11101 -0.0174 0.5362 1.0000
9.750 0.3838 0.12584 0.11606 -0.0193 0.5298 1.0000
10.000 0.3647 0.12581 0.11604 -0.0176 0.5177 1.0000
10.250 0.4186 0.13220 0.12246 -0.0204 0.5095 1.0000
10.500 0.3827 0.13115 0.12139 -0.0181 0.5003 1.0000
10.750 0.4137 0.13502 0.12530 -0.0192 0.4905 1.0000
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Polar data table (+)
Polar graphs
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