NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 500,000 Max Cl/Cd: 98.55 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651412-il-500000.txt Download as CSV file: xf-naca651412-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4399 0.08395 0.08170 -0.0529 1.0000 0.0228
-9.750 -0.4472 0.07908 0.07686 -0.0553 1.0000 0.0233
-9.500 -0.4634 0.07253 0.07038 -0.0595 1.0000 0.0232
-9.250 -0.4935 0.06734 0.06522 -0.0615 0.9994 0.0231
-9.000 -0.4972 0.05930 0.05701 -0.0727 0.9883 0.0232
-8.750 -0.4902 0.05286 0.05034 -0.0795 0.9802 0.0241
-8.500 -0.4745 0.04787 0.04473 -0.0842 0.9724 0.0264
-8.250 -0.4602 0.04384 0.04034 -0.0864 0.9644 0.0265
-8.000 -0.4553 0.03527 0.03144 -0.0890 0.9567 0.0277
-7.750 -0.4356 0.03331 0.02942 -0.0894 0.9476 0.0284
-7.500 -0.4142 0.03128 0.02722 -0.0899 0.9402 0.0295
-7.250 -0.4011 0.02630 0.02154 -0.0874 0.9290 0.0256
-7.000 -0.3854 0.02237 0.01718 -0.0862 0.9200 0.0240
-6.750 -0.3635 0.02010 0.01458 -0.0853 0.9127 0.0240
-6.500 -0.3405 0.01852 0.01276 -0.0846 0.9048 0.0244
-6.250 -0.3155 0.01763 0.01166 -0.0841 0.8978 0.0255
-6.000 -0.2904 0.01700 0.01087 -0.0836 0.8904 0.0262
-5.750 -0.2656 0.01583 0.00954 -0.0831 0.8836 0.0268
-5.500 -0.2423 0.01419 0.00783 -0.0824 0.8771 0.0277
-5.250 -0.2181 0.01340 0.00700 -0.0820 0.8701 0.0288
-5.000 -0.1927 0.01292 0.00647 -0.0817 0.8638 0.0302
-4.750 -0.1675 0.01245 0.00597 -0.0813 0.8567 0.0319
-4.500 -0.1420 0.01196 0.00540 -0.0810 0.8508 0.0331
-4.250 -0.1163 0.01158 0.00496 -0.0807 0.8439 0.0342
-4.000 -0.0917 0.01089 0.00418 -0.0804 0.8380 0.0362
-3.750 -0.0657 0.01048 0.00376 -0.0803 0.8318 0.0396
-3.500 -0.0389 0.01020 0.00343 -0.0803 0.8255 0.0429
-3.250 -0.0118 0.00988 0.00303 -0.0802 0.8201 0.0481
-3.000 0.0151 0.00957 0.00274 -0.0802 0.8139 0.0613
-2.750 0.0374 0.00774 0.00219 -0.0808 0.8084 0.4039
-2.500 0.0629 0.00713 0.00217 -0.0809 0.8028 0.5917
-2.250 0.0906 0.00708 0.00217 -0.0809 0.7970 0.6300
-2.000 0.1187 0.00709 0.00218 -0.0809 0.7922 0.6557
-1.750 0.1462 0.00713 0.00225 -0.0807 0.7866 0.6836
-1.500 0.1736 0.00722 0.00236 -0.0805 0.7813 0.7104
-1.250 0.2014 0.00732 0.00242 -0.0803 0.7767 0.7256
-1.000 0.2289 0.00734 0.00248 -0.0802 0.7711 0.7356
-0.750 0.2574 0.00735 0.00244 -0.0804 0.7661 0.7414
-0.500 0.2858 0.00737 0.00243 -0.0806 0.7617 0.7460
-0.250 0.3141 0.00738 0.00245 -0.0808 0.7564 0.7515
0.000 0.3426 0.00739 0.00244 -0.0810 0.7515 0.7567
0.250 0.3710 0.00743 0.00245 -0.0811 0.7473 0.7615
0.500 0.3992 0.00745 0.00249 -0.0813 0.7423 0.7672
0.750 0.4275 0.00747 0.00252 -0.0815 0.7375 0.7724
1.000 0.4558 0.00752 0.00256 -0.0816 0.7333 0.7777
1.250 0.4841 0.00756 0.00263 -0.0818 0.7287 0.7837
1.500 0.5121 0.00758 0.00270 -0.0819 0.7238 0.7889
1.750 0.5403 0.00764 0.00276 -0.0821 0.7195 0.7947
2.000 0.5685 0.00769 0.00284 -0.0822 0.7143 0.8011
2.250 0.5957 0.00770 0.00289 -0.0821 0.7075 0.8063
2.500 0.6230 0.00772 0.00294 -0.0820 0.6986 0.8129
2.750 0.6496 0.00772 0.00293 -0.0817 0.6874 0.8190
3.000 0.6756 0.00772 0.00294 -0.0812 0.6735 0.8256
3.250 0.7011 0.00770 0.00295 -0.0807 0.6543 0.8323
3.500 0.7263 0.00773 0.00300 -0.0801 0.6359 0.8388
3.750 0.7518 0.00781 0.00306 -0.0796 0.6161 0.8464
4.000 0.7761 0.00790 0.00316 -0.0788 0.5919 0.8533
4.250 0.7992 0.00811 0.00329 -0.0779 0.5536 0.8614
4.500 0.8139 0.00876 0.00354 -0.0755 0.4542 0.8695
4.750 0.8174 0.01042 0.00433 -0.0716 0.2761 0.8795
5.000 0.8222 0.01206 0.00519 -0.0681 0.1189 0.8908
5.250 0.8331 0.01310 0.00587 -0.0653 0.0499 0.9021
5.500 0.8504 0.01356 0.00636 -0.0634 0.0402 0.9134
5.750 0.8646 0.01415 0.00697 -0.0609 0.0340 0.9270
6.000 0.8806 0.01443 0.00734 -0.0586 0.0319 0.9434
6.250 0.8972 0.01479 0.00778 -0.0566 0.0295 0.9699
6.500 0.9194 0.01561 0.00863 -0.0563 0.0271 1.0000
6.750 0.9357 0.01663 0.00971 -0.0548 0.0257 1.0000
7.000 0.9554 0.01724 0.01037 -0.0538 0.0248 1.0000
7.250 0.9734 0.01793 0.01109 -0.0525 0.0237 1.0000
7.500 0.9911 0.01863 0.01183 -0.0512 0.0227 1.0000
7.750 1.0081 0.01939 0.01261 -0.0498 0.0217 1.0000
8.000 1.0240 0.02035 0.01359 -0.0483 0.0210 1.0000
8.250 1.0402 0.02173 0.01500 -0.0470 0.0203 1.0000
8.500 1.0663 0.02381 0.01714 -0.0472 0.0197 1.0000
8.750 1.0889 0.02478 0.01821 -0.0467 0.0194 1.0000
9.000 1.1130 0.02597 0.01950 -0.0464 0.0191 1.0000
9.250 1.1372 0.02730 0.02097 -0.0462 0.0186 1.0000
9.500 1.1587 0.02856 0.02235 -0.0457 0.0180 1.0000
9.750 1.1817 0.03027 0.02423 -0.0454 0.0175 1.0000
10.000 1.2028 0.03224 0.02640 -0.0449 0.0172 1.0000
10.250 1.2211 0.03472 0.02913 -0.0440 0.0171 1.0000
10.500 1.2344 0.03776 0.03248 -0.0425 0.0171 1.0000
10.750 1.2380 0.04163 0.03674 -0.0398 0.0174 1.0000
11.000 1.2316 0.04570 0.04117 -0.0360 0.0179 1.0000
11.250 1.2208 0.04952 0.04528 -0.0322 0.0183 1.0000
11.500 1.2072 0.05300 0.04902 -0.0286 0.0185 1.0000
11.750 1.1906 0.05684 0.05308 -0.0256 0.0187 1.0000
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Polar data table (+)
Polar graphs
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