NACA 64(3)-218 (naca643218-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(3)-218 (naca643218-il) Reynolds number: 100,000 Max Cl/Cd: 39.67 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca643218-il-100000-n5.txt Download as CSV file: xf-naca643218-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-218
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7257 0.10371 0.09773 -0.0431 1.0000 0.0409
-15.750 -0.7877 0.08925 0.08289 -0.0519 1.0000 0.0404
-15.500 -0.8158 0.08180 0.07518 -0.0558 1.0000 0.0404
-15.250 -0.8347 0.07613 0.06928 -0.0584 1.0000 0.0404
-15.000 -0.8483 0.07145 0.06440 -0.0601 1.0000 0.0407
-14.750 -0.8582 0.06739 0.06014 -0.0614 1.0000 0.0410
-14.500 -0.8650 0.06376 0.05631 -0.0622 1.0000 0.0414
-14.250 -0.8692 0.06048 0.05283 -0.0627 1.0000 0.0418
-14.000 -0.8707 0.05749 0.04964 -0.0630 1.0000 0.0424
-13.750 -0.8700 0.05477 0.04671 -0.0631 1.0000 0.0430
-13.500 -0.8690 0.05217 0.04386 -0.0630 1.0000 0.0439
-13.250 -0.8616 0.05005 0.04158 -0.0628 1.0000 0.0448
-13.000 -0.8489 0.04849 0.04004 -0.0626 1.0000 0.0457
-12.750 -0.8380 0.04690 0.03840 -0.0623 1.0000 0.0468
-12.500 -0.8257 0.04532 0.03674 -0.0619 1.0000 0.0480
-12.250 -0.8117 0.04380 0.03510 -0.0614 1.0000 0.0493
-12.000 -0.7966 0.04238 0.03352 -0.0609 1.0000 0.0506
-11.750 -0.7807 0.04115 0.03231 -0.0604 1.0000 0.0521
-11.500 -0.7668 0.03996 0.03115 -0.0599 1.0000 0.0537
-11.250 -0.7530 0.03880 0.02996 -0.0593 1.0000 0.0558
-11.000 -0.7376 0.03774 0.02881 -0.0586 1.0000 0.0578
-10.750 -0.7236 0.03667 0.02778 -0.0578 1.0000 0.0597
-10.500 -0.7121 0.03561 0.02678 -0.0569 1.0000 0.0618
-10.250 -0.7017 0.03464 0.02581 -0.0558 1.0000 0.0646
-10.000 -0.6935 0.03380 0.02495 -0.0542 1.0000 0.0673
-9.750 -0.6725 0.03250 0.02372 -0.0556 0.9776 0.0711
-9.500 -0.6441 0.03133 0.02246 -0.0579 0.9603 0.0768
-9.250 -0.6197 0.02997 0.02114 -0.0599 0.9447 0.0830
-9.000 -0.5981 0.02872 0.01987 -0.0612 0.9292 0.0910
-8.750 -0.5810 0.02759 0.01871 -0.0614 0.9135 0.1006
-8.500 -0.5697 0.02648 0.01760 -0.0606 0.8983 0.1122
-8.250 -0.5624 0.02538 0.01653 -0.0591 0.8839 0.1262
-8.000 -0.5585 0.02429 0.01549 -0.0569 0.8705 0.1438
-7.750 -0.5585 0.02330 0.01457 -0.0539 0.8585 0.1656
-7.500 -0.5576 0.02233 0.01374 -0.0510 0.8462 0.1956
-7.250 -0.5557 0.02126 0.01287 -0.0481 0.8360 0.2393
-7.000 -0.5539 0.02017 0.01213 -0.0451 0.8259 0.3007
-6.750 -0.5454 0.01956 0.01204 -0.0423 0.8172 0.3805
-6.500 -0.5272 0.01951 0.01211 -0.0407 0.8089 0.4413
-6.250 -0.5070 0.01948 0.01197 -0.0394 0.8020 0.4744
-6.000 -0.4847 0.01961 0.01204 -0.0384 0.7936 0.4977
-5.750 -0.4611 0.01973 0.01205 -0.0374 0.7873 0.5167
-5.500 -0.4369 0.01993 0.01215 -0.0365 0.7802 0.5323
-5.250 -0.4124 0.02010 0.01222 -0.0357 0.7730 0.5463
-5.000 -0.3881 0.02021 0.01218 -0.0348 0.7675 0.5604
-4.750 -0.3618 0.02062 0.01258 -0.0340 0.7601 0.5729
-4.500 -0.3348 0.02097 0.01288 -0.0332 0.7538 0.5834
-4.250 -0.3112 0.02086 0.01258 -0.0326 0.7489 0.5945
-4.000 -0.2838 0.02101 0.01272 -0.0322 0.7423 0.5988
-3.750 -0.2572 0.02099 0.01261 -0.0320 0.7365 0.6033
-3.500 -0.2318 0.02075 0.01223 -0.0318 0.7317 0.6090
-3.250 -0.2070 0.02054 0.01189 -0.0317 0.7259 0.6141
-3.000 -0.1802 0.02053 0.01185 -0.0315 0.7199 0.6173
-2.750 -0.1532 0.02044 0.01168 -0.0313 0.7150 0.6212
-2.500 -0.1269 0.02028 0.01140 -0.0313 0.7105 0.6261
-2.250 -0.1023 0.02010 0.01114 -0.0314 0.7043 0.6315
-2.000 -0.0751 0.02009 0.01110 -0.0313 0.6996 0.6343
-1.750 -0.0476 0.02002 0.01096 -0.0312 0.6957 0.6374
-1.500 -0.0209 0.01997 0.01086 -0.0313 0.6915 0.6414
-1.250 0.0046 0.01990 0.01075 -0.0314 0.6861 0.6461
-1.000 0.0313 0.01978 0.01056 -0.0316 0.6817 0.6501
-0.750 0.0591 0.01975 0.01050 -0.0316 0.6780 0.6528
-0.500 0.0862 0.01975 0.01048 -0.0315 0.6741 0.6563
-0.250 0.1116 0.01981 0.01056 -0.0315 0.6688 0.6606
0.000 0.1382 0.01978 0.01049 -0.0317 0.6646 0.6656
0.250 0.1657 0.01976 0.01045 -0.0319 0.6613 0.6693
0.500 0.1938 0.01978 0.01046 -0.0319 0.6585 0.6725
0.750 0.2191 0.01993 0.01066 -0.0318 0.6543 0.6764
1.000 0.2445 0.02004 0.01081 -0.0318 0.6498 0.6811
1.250 0.2715 0.02008 0.01083 -0.0321 0.6459 0.6865
1.500 0.2986 0.02014 0.01093 -0.0319 0.6428 0.6902
1.750 0.3267 0.02020 0.01101 -0.0319 0.6403 0.6947
2.000 0.3505 0.02046 0.01135 -0.0318 0.6360 0.7002
2.250 0.3753 0.02066 0.01161 -0.0318 0.6316 0.7056
2.500 0.4010 0.02081 0.01183 -0.0315 0.6280 0.7096
2.750 0.4283 0.02090 0.01197 -0.0315 0.6250 0.7145
3.000 0.4574 0.02094 0.01201 -0.0318 0.6225 0.7205
3.250 0.4780 0.02133 0.01254 -0.0311 0.6169 0.7258
3.500 0.5014 0.02158 0.01290 -0.0306 0.6123 0.7311
3.750 0.5282 0.02170 0.01308 -0.0306 0.6087 0.7378
4.000 0.5568 0.02173 0.01316 -0.0307 0.6057 0.7440
4.250 0.5781 0.02210 0.01367 -0.0299 0.6011 0.7497
4.500 0.5992 0.02247 0.01418 -0.0292 0.5956 0.7569
4.750 0.6251 0.02259 0.01439 -0.0290 0.5915 0.7631
5.000 0.6538 0.02257 0.01443 -0.0289 0.5881 0.7692
5.250 0.6727 0.02298 0.01499 -0.0279 0.5814 0.7774
5.500 0.6965 0.02296 0.01509 -0.0270 0.5744 0.7839
5.750 0.7266 0.02262 0.01480 -0.0268 0.5676 0.7916
6.000 0.7458 0.02266 0.01497 -0.0254 0.5569 0.7998
6.250 0.7696 0.02243 0.01483 -0.0243 0.5467 0.8076
6.500 0.7968 0.02205 0.01450 -0.0237 0.5360 0.8164
6.750 0.8116 0.02217 0.01480 -0.0215 0.5239 0.8252
7.000 0.8321 0.02206 0.01478 -0.0201 0.5117 0.8348
7.250 0.8514 0.02190 0.01471 -0.0183 0.4979 0.8447
7.500 0.8658 0.02188 0.01481 -0.0160 0.4816 0.8555
7.750 0.8752 0.02206 0.01511 -0.0131 0.4625 0.8685
8.000 0.8789 0.02234 0.01551 -0.0095 0.4405 0.8832
8.250 0.8790 0.02270 0.01594 -0.0054 0.4132 0.9010
8.500 0.8856 0.02295 0.01604 -0.0023 0.3697 0.9225
8.750 0.8919 0.02389 0.01665 -0.0005 0.3156 0.9538
9.000 0.8914 0.02560 0.01806 0.0006 0.2676 1.0000
9.250 0.8881 0.02762 0.01981 0.0021 0.2306 1.0000
9.500 0.8860 0.02972 0.02170 0.0033 0.1996 1.0000
9.750 0.8852 0.03184 0.02363 0.0043 0.1734 1.0000
10.000 0.8873 0.03385 0.02550 0.0050 0.1506 1.0000
10.250 0.8902 0.03583 0.02737 0.0057 0.1324 1.0000
10.500 0.8943 0.03777 0.02921 0.0063 0.1175 1.0000
10.750 0.8997 0.03965 0.03102 0.0069 0.1050 1.0000
11.000 0.9063 0.04146 0.03280 0.0074 0.0952 1.0000
11.250 0.9126 0.04331 0.03460 0.0078 0.0872 1.0000
11.500 0.9190 0.04520 0.03646 0.0082 0.0807 1.0000
11.750 0.9273 0.04695 0.03823 0.0085 0.0749 1.0000
12.000 0.9342 0.04886 0.04012 0.0088 0.0705 1.0000
12.250 0.9434 0.05061 0.04189 0.0091 0.0662 1.0000
12.500 0.9518 0.05245 0.04375 0.0093 0.0627 1.0000
12.750 0.9601 0.05432 0.04562 0.0094 0.0598 1.0000
13.000 0.9706 0.05604 0.04741 0.0096 0.0568 1.0000
13.250 0.9795 0.05793 0.04931 0.0097 0.0544 1.0000
13.500 0.9890 0.05979 0.05118 0.0098 0.0522 1.0000
13.750 1.0000 0.06156 0.05306 0.0099 0.0500 1.0000
14.000 1.0098 0.06346 0.05502 0.0099 0.0481 1.0000
14.250 1.0196 0.06536 0.05690 0.0099 0.0467 1.0000
14.500 1.0291 0.06742 0.05906 0.0098 0.0449 1.0000
14.750 1.0378 0.06961 0.06139 0.0096 0.0433 1.0000
15.000 1.0466 0.07179 0.06367 0.0094 0.0421 1.0000
15.250 1.0550 0.07402 0.06594 0.0091 0.0410 1.0000
15.500 1.0659 0.07597 0.06788 0.0090 0.0402 1.0000
15.750 1.0708 0.07883 0.07094 0.0085 0.0393 1.0000
16.000 1.0733 0.08206 0.07439 0.0078 0.0384 1.0000
16.250 1.0741 0.08550 0.07802 0.0069 0.0375 1.0000
16.500 1.0738 0.08911 0.08179 0.0057 0.0367 1.0000
16.750 1.0733 0.09277 0.08559 0.0044 0.0361 1.0000
17.000 1.0731 0.09643 0.08937 0.0030 0.0355 1.0000
17.250 1.0740 0.09992 0.09294 0.0016 0.0350 1.0000
17.500 1.0735 0.10375 0.09685 0.0001 0.0345 1.0000
17.750 1.0579 0.11026 0.10366 -0.0031 0.0343 1.0000
18.000 1.0396 0.11752 0.11121 -0.0071 0.0341 1.0000
18.250 1.0185 0.12568 0.11963 -0.0118 0.0340 1.0000
18.500 0.9888 0.13619 0.13043 -0.0183 0.0340 1.0000
18.750 0.9390 0.15262 0.14718 -0.0290 0.0342 1.0000
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