NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 200,000 Max Cl/Cd: 59.66 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632a015-il-200000.txt Download as CSV file: xf-naca632a015-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4778 0.09173 0.08806 -0.0428 1.0000 0.0508
-10.750 -0.5006 0.08393 0.08025 -0.0485 1.0000 0.0510
-10.500 -0.5292 0.07772 0.07397 -0.0523 1.0000 0.0513
-10.250 -0.5491 0.07343 0.06963 -0.0534 1.0000 0.0509
-10.000 -0.5768 0.06979 0.06590 -0.0529 1.0000 0.0514
-9.750 -0.5972 0.06705 0.06309 -0.0507 1.0000 0.0513
-9.500 -0.6258 0.06527 0.06122 -0.0457 1.0000 0.0519
-9.250 -0.6683 0.06549 0.06110 -0.0378 1.0000 0.0532
-9.000 -0.6941 0.06503 0.06038 -0.0314 1.0000 0.0535
-8.750 -0.7163 0.06452 0.05964 -0.0248 1.0000 0.0537
-8.500 -0.7130 0.05768 0.05300 -0.0239 1.0000 0.0546
-8.250 -0.7227 0.05570 0.05108 -0.0194 1.0000 0.0550
-8.000 -0.6960 0.05202 0.04741 -0.0220 0.9954 0.0568
-7.750 -0.6698 0.04894 0.04411 -0.0243 0.9879 0.0596
-7.500 -0.6520 0.04583 0.04041 -0.0250 0.9777 0.0650
-7.250 -0.6194 0.04260 0.03726 -0.0279 0.9726 0.0689
-7.000 -0.5984 0.04039 0.03458 -0.0282 0.9626 0.0771
-6.750 -0.5618 0.03103 0.02367 -0.0250 0.9582 0.0385
-6.500 -0.5249 0.02789 0.02035 -0.0269 0.9532 0.0382
-6.250 -0.4871 0.02527 0.01751 -0.0289 0.9476 0.0392
-6.000 -0.4458 0.02394 0.01626 -0.0320 0.9433 0.0424
-5.750 -0.4076 0.02246 0.01455 -0.0336 0.9363 0.0447
-5.500 -0.3672 0.02059 0.01267 -0.0360 0.9300 0.0472
-5.250 -0.3295 0.01967 0.01172 -0.0380 0.9228 0.0525
-5.000 -0.2983 0.01837 0.01048 -0.0388 0.9127 0.0576
-4.750 -0.2692 0.01777 0.00979 -0.0389 0.9018 0.0634
-4.500 -0.2446 0.01674 0.00883 -0.0385 0.8919 0.0706
-4.250 -0.2255 0.01621 0.00825 -0.0368 0.8789 0.0764
-4.000 -0.2071 0.01568 0.00774 -0.0351 0.8672 0.0839
-3.750 -0.1873 0.01515 0.00714 -0.0335 0.8572 0.0911
-3.500 -0.1700 0.01472 0.00667 -0.0315 0.8456 0.0987
-3.250 -0.1513 0.01428 0.00618 -0.0297 0.8356 0.1125
-3.000 -0.1481 0.01274 0.00543 -0.0255 0.8256 0.3047
-2.750 -0.1540 0.01164 0.00557 -0.0187 0.8149 0.5891
-2.500 -0.1338 0.01173 0.00570 -0.0164 0.8073 0.6489
-2.250 -0.1125 0.01186 0.00588 -0.0146 0.7974 0.6772
-2.000 -0.0874 0.01197 0.00590 -0.0135 0.7902 0.6988
-1.750 -0.0646 0.01209 0.00601 -0.0122 0.7808 0.7157
-1.500 -0.0388 0.01220 0.00607 -0.0112 0.7736 0.7334
-1.250 -0.0166 0.01236 0.00625 -0.0096 0.7645 0.7521
-1.000 0.0093 0.01251 0.00640 -0.0085 0.7574 0.7704
-0.750 0.0345 0.01261 0.00652 -0.0076 0.7489 0.7829
-0.500 0.0618 0.01259 0.00644 -0.0072 0.7413 0.7910
-0.250 0.0874 0.01260 0.00643 -0.0067 0.7332 0.7997
0.000 0.1141 0.01256 0.00633 -0.0062 0.7244 0.8079
0.250 0.1392 0.01252 0.00626 -0.0054 0.7136 0.8168
0.500 0.1663 0.01243 0.00609 -0.0049 0.7031 0.8251
0.750 0.1916 0.01237 0.00601 -0.0042 0.6918 0.8342
1.000 0.2180 0.01235 0.00598 -0.0037 0.6826 0.8429
1.250 0.2447 0.01235 0.00594 -0.0032 0.6741 0.8525
1.500 0.2720 0.01237 0.00597 -0.0030 0.6650 0.8608
1.750 0.2987 0.01237 0.00592 -0.0025 0.6565 0.8708
2.000 0.3276 0.01242 0.00600 -0.0026 0.6467 0.8789
2.250 0.3543 0.01243 0.00595 -0.0021 0.6384 0.8895
2.500 0.3864 0.01251 0.00608 -0.0029 0.6277 0.8965
2.750 0.4133 0.01255 0.00608 -0.0025 0.6185 0.9073
3.000 0.4501 0.01264 0.00616 -0.0042 0.6069 0.9129
3.250 0.4780 0.01270 0.00625 -0.0041 0.5957 0.9233
3.500 0.5177 0.01281 0.00634 -0.0065 0.5839 0.9280
3.750 0.5549 0.01291 0.00640 -0.0083 0.5707 0.9343
4.000 0.5884 0.01298 0.00647 -0.0095 0.5560 0.9421
4.250 0.6301 0.01310 0.00656 -0.0124 0.5393 0.9461
4.500 0.6645 0.01321 0.00667 -0.0138 0.5217 0.9538
4.750 0.7025 0.01333 0.00679 -0.0161 0.4989 0.9594
5.000 0.7392 0.01351 0.00688 -0.0181 0.4739 0.9661
5.250 0.7741 0.01371 0.00702 -0.0199 0.4434 0.9733
5.500 0.8090 0.01402 0.00719 -0.0218 0.4075 0.9808
5.750 0.8452 0.01443 0.00744 -0.0242 0.3704 0.9874
6.000 0.8814 0.01494 0.00776 -0.0267 0.3415 0.9945
6.250 0.9181 0.01539 0.00809 -0.0294 0.3189 1.0000
6.500 0.9248 0.01568 0.00832 -0.0260 0.3068 1.0000
6.750 0.9312 0.01602 0.00856 -0.0226 0.2964 1.0000
7.000 0.9397 0.01632 0.00885 -0.0194 0.2861 1.0000
7.250 0.9492 0.01668 0.00918 -0.0164 0.2768 1.0000
7.500 0.9596 0.01708 0.00952 -0.0135 0.2678 1.0000
7.750 0.9716 0.01743 0.00989 -0.0108 0.2587 1.0000
8.000 0.9837 0.01792 0.01028 -0.0083 0.2506 1.0000
8.250 0.9970 0.01825 0.01070 -0.0059 0.2424 1.0000
8.500 1.0102 0.01877 0.01114 -0.0036 0.2352 1.0000
8.750 1.0237 0.01915 0.01160 -0.0012 0.2277 1.0000
9.000 1.0366 0.01964 0.01205 0.0011 0.2206 1.0000
9.250 1.0492 0.02009 0.01258 0.0035 0.2133 1.0000
9.500 1.0601 0.02057 0.01305 0.0061 0.2059 1.0000
9.750 1.0686 0.02103 0.01357 0.0092 0.1984 1.0000
10.000 1.0747 0.02147 0.01401 0.0126 0.1907 1.0000
10.250 1.0817 0.02197 0.01458 0.0157 0.1824 1.0000
10.500 1.0881 0.02257 0.01515 0.0186 0.1743 1.0000
10.750 1.0957 0.02315 0.01585 0.0211 0.1652 1.0000
11.000 1.1019 0.02393 0.01661 0.0236 0.1569 1.0000
11.250 1.1087 0.02473 0.01747 0.0258 0.1477 1.0000
11.500 1.1153 0.02568 0.01847 0.0278 0.1381 1.0000
11.750 1.1197 0.02684 0.01961 0.0297 0.1295 1.0000
12.000 1.1243 0.02808 0.02086 0.0314 0.1205 1.0000
12.250 1.1297 0.02943 0.02226 0.0329 0.1124 1.0000
12.500 1.1315 0.03108 0.02382 0.0345 0.1062 1.0000
12.750 1.1376 0.03254 0.02539 0.0356 0.0999 1.0000
13.000 1.1393 0.03437 0.02714 0.0369 0.0949 1.0000
13.250 1.1453 0.03596 0.02886 0.0379 0.0903 1.0000
13.500 1.1490 0.03775 0.03068 0.0387 0.0862 1.0000
13.750 1.1525 0.03964 0.03255 0.0397 0.0823 1.0000
14.000 1.1566 0.04152 0.03457 0.0403 0.0787 1.0000
14.250 1.1598 0.04349 0.03657 0.0408 0.0755 1.0000
14.500 1.1646 0.04541 0.03844 0.0416 0.0723 1.0000
14.750 1.1673 0.04756 0.04077 0.0420 0.0699 1.0000
15.000 1.1706 0.04970 0.04300 0.0423 0.0674 1.0000
15.250 1.1749 0.05174 0.04505 0.0426 0.0653 1.0000
15.500 1.1850 0.05339 0.04664 0.0434 0.0630 1.0000
15.750 1.1833 0.05616 0.04962 0.0432 0.0615 1.0000
16.000 1.1834 0.05884 0.05245 0.0431 0.0599 1.0000
16.250 1.1842 0.06147 0.05520 0.0429 0.0584 1.0000
16.500 1.1874 0.06388 0.05767 0.0427 0.0571 1.0000
16.750 1.1946 0.06590 0.05968 0.0428 0.0557 1.0000
17.000 1.2001 0.06837 0.06222 0.0432 0.0544 1.0000
17.250 1.1918 0.07229 0.06637 0.0421 0.0538 1.0000
17.500 1.1826 0.07648 0.07076 0.0408 0.0532 1.0000
17.750 1.1721 0.08102 0.07551 0.0391 0.0526 1.0000
18.000 1.1594 0.08600 0.08068 0.0371 0.0518 1.0000
18.250 1.1462 0.09128 0.08615 0.0348 0.0513 1.0000
18.500 1.1302 0.09717 0.09223 0.0320 0.0509 1.0000
18.750 1.1096 0.10410 0.09935 0.0285 0.0505 1.0000
19.000 1.0811 0.11274 0.10822 0.0237 0.0505 1.0000
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