NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 50,000 Max Cl/Cd: 29.65 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632a015-il-50000-n5.txt Download as CSV file: xf-naca632a015-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4934 0.10538 0.09780 -0.0415 1.0000 0.0535
-11.500 -0.4937 0.10091 0.09337 -0.0429 1.0000 0.0530
-11.250 -0.4991 0.09596 0.08844 -0.0449 1.0000 0.0523
-11.000 -0.5099 0.09075 0.08324 -0.0474 1.0000 0.0516
-10.750 -0.5265 0.08552 0.07800 -0.0497 1.0000 0.0509
-10.500 -0.5466 0.08076 0.07319 -0.0513 1.0000 0.0504
-10.250 -0.5666 0.07678 0.06915 -0.0516 1.0000 0.0497
-10.000 -0.5883 0.07328 0.06556 -0.0506 1.0000 0.0493
-9.750 -0.6086 0.07044 0.06264 -0.0481 1.0000 0.0489
-9.500 -0.6281 0.06782 0.05992 -0.0446 1.0000 0.0485
-9.250 -0.6431 0.06512 0.05706 -0.0412 1.0000 0.0482
-9.000 -0.6548 0.06253 0.05430 -0.0377 1.0000 0.0479
-8.750 -0.6641 0.05995 0.05152 -0.0340 1.0000 0.0477
-8.500 -0.6702 0.05753 0.04889 -0.0304 1.0000 0.0476
-8.250 -0.6744 0.05520 0.04635 -0.0267 1.0000 0.0476
-8.000 -0.6766 0.05303 0.04396 -0.0231 1.0000 0.0477
-7.750 -0.6773 0.05107 0.04182 -0.0195 1.0000 0.0481
-7.500 -0.6771 0.04933 0.03988 -0.0158 1.0000 0.0491
-7.250 -0.6765 0.04765 0.03798 -0.0122 1.0000 0.0501
-7.000 -0.6746 0.04603 0.03610 -0.0086 1.0000 0.0511
-6.750 -0.6712 0.04441 0.03417 -0.0050 1.0000 0.0523
-6.500 -0.6620 0.04275 0.03216 -0.0023 0.9992 0.0531
-6.250 -0.6268 0.04019 0.02931 -0.0042 0.9914 0.0546
-6.000 -0.5894 0.03820 0.02724 -0.0066 0.9839 0.0576
-5.750 -0.5519 0.03652 0.02528 -0.0084 0.9758 0.0618
-5.500 -0.5068 0.03472 0.02342 -0.0112 0.9706 0.0660
-5.250 -0.4666 0.03347 0.02211 -0.0131 0.9629 0.0726
-5.000 -0.4236 0.03219 0.02086 -0.0156 0.9571 0.0805
-4.750 -0.3910 0.03129 0.01979 -0.0165 0.9476 0.0885
-4.500 -0.3613 0.03006 0.01858 -0.0176 0.9389 0.0967
-4.250 -0.3358 0.02903 0.01746 -0.0179 0.9285 0.1060
-4.000 -0.3121 0.02807 0.01639 -0.0179 0.9182 0.1167
-3.750 -0.2841 0.02683 0.01516 -0.0188 0.9098 0.1360
-3.500 -0.2730 0.02497 0.01400 -0.0174 0.8982 0.2084
-3.250 -0.2669 0.02378 0.01466 -0.0125 0.8889 0.5815
-3.000 -0.2459 0.02428 0.01521 -0.0095 0.8790 0.6574
-2.750 -0.2217 0.02485 0.01570 -0.0071 0.8699 0.7041
-2.500 -0.1913 0.02577 0.01660 -0.0049 0.8621 0.7494
-2.250 -0.1378 0.02706 0.01777 -0.0058 0.8581 0.7895
-2.000 -0.1106 0.02708 0.01761 -0.0057 0.8475 0.7992
-1.750 -0.0721 0.02687 0.01719 -0.0078 0.8411 0.8071
-1.500 -0.0458 0.02686 0.01706 -0.0078 0.8303 0.8153
-1.250 -0.0089 0.02666 0.01668 -0.0095 0.8239 0.8236
-1.000 0.0190 0.02673 0.01666 -0.0098 0.8133 0.8317
-0.750 0.0546 0.02655 0.01634 -0.0113 0.8068 0.8403
-0.500 0.0835 0.02668 0.01640 -0.0119 0.7963 0.8482
-0.250 0.1185 0.02653 0.01613 -0.0132 0.7898 0.8572
0.000 0.1489 0.02670 0.01627 -0.0141 0.7792 0.8649
0.250 0.1841 0.02657 0.01604 -0.0154 0.7726 0.8741
0.500 0.2164 0.02677 0.01622 -0.0167 0.7617 0.8817
0.750 0.2487 0.02671 0.01611 -0.0176 0.7538 0.8911
1.000 0.2876 0.02680 0.01619 -0.0199 0.7431 0.8979
1.250 0.3163 0.02683 0.01619 -0.0203 0.7326 0.9080
1.500 0.3620 0.02663 0.01595 -0.0234 0.7225 0.9138
1.750 0.3884 0.02666 0.01599 -0.0234 0.7091 0.9245
2.000 0.4276 0.02653 0.01585 -0.0255 0.6953 0.9314
2.250 0.4592 0.02638 0.01569 -0.0261 0.6818 0.9413
2.500 0.4990 0.02612 0.01543 -0.0282 0.6682 0.9487
2.750 0.5331 0.02592 0.01523 -0.0293 0.6550 0.9578
3.000 0.5678 0.02583 0.01517 -0.0309 0.6399 0.9669
3.250 0.6024 0.02574 0.01513 -0.0325 0.6249 0.9760
3.500 0.6371 0.02563 0.01509 -0.0341 0.6094 0.9854
3.750 0.6733 0.02550 0.01499 -0.0361 0.5929 0.9948
4.000 0.6991 0.02543 0.01496 -0.0362 0.5767 1.0000
4.250 0.7096 0.02548 0.01505 -0.0334 0.5619 1.0000
4.500 0.7200 0.02554 0.01511 -0.0305 0.5467 1.0000
4.750 0.7302 0.02561 0.01519 -0.0275 0.5309 1.0000
5.000 0.7405 0.02572 0.01529 -0.0246 0.5148 1.0000
5.250 0.7508 0.02587 0.01544 -0.0216 0.4982 1.0000
5.500 0.7612 0.02606 0.01561 -0.0186 0.4809 1.0000
5.750 0.7721 0.02629 0.01581 -0.0157 0.4634 1.0000
6.000 0.7837 0.02656 0.01604 -0.0129 0.4458 1.0000
6.250 0.7960 0.02689 0.01633 -0.0103 0.4288 1.0000
6.500 0.8086 0.02727 0.01665 -0.0078 0.4121 1.0000
6.750 0.8215 0.02771 0.01704 -0.0054 0.3961 1.0000
7.000 0.8345 0.02822 0.01751 -0.0030 0.3809 1.0000
7.250 0.8476 0.02879 0.01806 -0.0008 0.3668 1.0000
7.500 0.8612 0.02940 0.01863 0.0014 0.3534 1.0000
7.750 0.8758 0.03003 0.01921 0.0034 0.3411 1.0000
8.000 0.8919 0.03063 0.01975 0.0051 0.3292 1.0000
8.250 0.9038 0.03142 0.02058 0.0073 0.3171 1.0000
8.500 0.9167 0.03223 0.02143 0.0092 0.3059 1.0000
8.750 0.9327 0.03298 0.02214 0.0108 0.2954 1.0000
9.000 0.9453 0.03385 0.02308 0.0127 0.2850 1.0000
9.250 0.9568 0.03481 0.02412 0.0147 0.2751 1.0000
9.500 0.9749 0.03559 0.02484 0.0159 0.2655 1.0000
9.750 0.9798 0.03673 0.02616 0.0185 0.2559 1.0000
10.000 0.9912 0.03769 0.02715 0.0204 0.2468 1.0000
10.250 0.9978 0.03869 0.02821 0.0228 0.2372 1.0000
10.500 0.9998 0.03993 0.02955 0.0255 0.2280 1.0000
10.750 1.0111 0.04079 0.03034 0.0271 0.2185 1.0000
11.000 1.0059 0.04246 0.03223 0.0299 0.2098 1.0000
11.250 1.0132 0.04364 0.03341 0.0315 0.2013 1.0000
11.500 1.0110 0.04546 0.03542 0.0335 0.1931 1.0000
11.750 1.0160 0.04697 0.03698 0.0349 0.1855 1.0000
12.000 1.0128 0.04912 0.03929 0.0363 0.1780 1.0000
12.250 1.0166 0.05087 0.04109 0.0373 0.1709 1.0000
12.500 1.0092 0.05363 0.04405 0.0383 0.1643 1.0000
12.750 1.0146 0.05530 0.04571 0.0391 0.1576 1.0000
13.000 0.9993 0.05923 0.04990 0.0393 0.1522 1.0000
13.250 1.0045 0.06109 0.05180 0.0398 0.1463 1.0000
13.500 0.9892 0.06544 0.05634 0.0394 0.1419 1.0000
13.750 0.9659 0.07108 0.06220 0.0381 0.1380 1.0000
14.000 0.9846 0.07124 0.06226 0.0390 0.1318 1.0000
14.250 0.9450 0.07970 0.07099 0.0360 0.1296 1.0000
14.500 0.8663 0.09619 0.08770 0.0281 0.1285 1.0000
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