NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-215 AIRFOIL (n63215-il) Reynolds number: 100,000 Max Cl/Cd: 46.49 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63215-il-100000-n5.txt Download as CSV file: xf-n63215-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-215 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6567 0.11452 0.10904 -0.0223 1.0000 0.0365
-14.250 -0.6990 0.09962 0.09405 -0.0315 1.0000 0.0359
-14.000 -0.7424 0.08722 0.08146 -0.0399 1.0000 0.0354
-13.750 -0.7744 0.07859 0.07264 -0.0455 1.0000 0.0351
-13.500 -0.8013 0.07167 0.06549 -0.0495 1.0000 0.0351
-13.250 -0.8231 0.06605 0.05964 -0.0523 1.0000 0.0352
-13.000 -0.8409 0.06130 0.05465 -0.0541 1.0000 0.0354
-12.750 -0.8566 0.05712 0.05021 -0.0552 1.0000 0.0357
-12.500 -0.8694 0.05347 0.04627 -0.0555 1.0000 0.0361
-12.250 -0.8812 0.05027 0.04274 -0.0552 1.0000 0.0367
-12.000 -0.8806 0.04772 0.04003 -0.0547 1.0000 0.0372
-11.750 -0.8738 0.04582 0.03809 -0.0542 1.0000 0.0380
-11.500 -0.8682 0.04389 0.03606 -0.0534 1.0000 0.0388
-11.250 -0.8616 0.04201 0.03404 -0.0524 1.0000 0.0396
-11.000 -0.8533 0.04016 0.03203 -0.0513 1.0000 0.0405
-10.750 -0.8429 0.03839 0.03007 -0.0501 1.0000 0.0415
-10.500 -0.8316 0.03676 0.02824 -0.0489 1.0000 0.0428
-10.250 -0.8184 0.03526 0.02652 -0.0477 1.0000 0.0442
-10.000 -0.8026 0.03395 0.02528 -0.0470 1.0000 0.0459
-9.750 -0.7878 0.03279 0.02410 -0.0459 1.0000 0.0476
-9.500 -0.7722 0.03162 0.02286 -0.0448 1.0000 0.0494
-9.250 -0.7575 0.03057 0.02169 -0.0434 1.0000 0.0515
-9.000 -0.7457 0.02955 0.02067 -0.0417 1.0000 0.0535
-8.750 -0.7400 0.02877 0.01995 -0.0390 1.0000 0.0553
-8.500 -0.7261 0.02792 0.01909 -0.0379 0.9936 0.0577
-8.250 -0.6934 0.02684 0.01787 -0.0399 0.9823 0.0618
-8.000 -0.6633 0.02562 0.01670 -0.0419 0.9712 0.0662
-7.750 -0.6325 0.02462 0.01561 -0.0436 0.9604 0.0715
-7.500 -0.6052 0.02356 0.01457 -0.0449 0.9487 0.0780
-7.250 -0.5782 0.02264 0.01360 -0.0458 0.9375 0.0866
-7.000 -0.5523 0.02172 0.01268 -0.0466 0.9270 0.0987
-6.750 -0.5302 0.02078 0.01184 -0.0466 0.9156 0.1176
-6.500 -0.5104 0.01986 0.01106 -0.0462 0.9040 0.1499
-6.250 -0.4914 0.01885 0.01030 -0.0456 0.8936 0.2020
-6.000 -0.4742 0.01783 0.00967 -0.0448 0.8833 0.2772
-5.750 -0.4560 0.01714 0.00938 -0.0437 0.8731 0.3582
-5.500 -0.4329 0.01686 0.00926 -0.0429 0.8651 0.4211
-5.250 -0.4099 0.01678 0.00923 -0.0420 0.8554 0.4633
-5.000 -0.3842 0.01679 0.00922 -0.0413 0.8483 0.4974
-4.750 -0.3597 0.01686 0.00923 -0.0405 0.8389 0.5245
-4.500 -0.3335 0.01696 0.00928 -0.0398 0.8322 0.5456
-4.250 -0.3081 0.01705 0.00931 -0.0391 0.8234 0.5626
-4.000 -0.2817 0.01710 0.00926 -0.0385 0.8165 0.5772
-3.750 -0.2559 0.01716 0.00924 -0.0379 0.8085 0.5912
-3.500 -0.2296 0.01718 0.00917 -0.0374 0.8013 0.6038
-3.250 -0.2030 0.01722 0.00915 -0.0368 0.7944 0.6120
-3.000 -0.1765 0.01714 0.00894 -0.0367 0.7867 0.6218
-2.750 -0.1494 0.01714 0.00888 -0.0361 0.7810 0.6282
-2.500 -0.1230 0.01709 0.00875 -0.0361 0.7727 0.6371
-2.250 -0.0960 0.01706 0.00867 -0.0356 0.7665 0.6433
-2.000 -0.0693 0.01704 0.00859 -0.0355 0.7594 0.6509
-1.750 -0.0424 0.01700 0.00849 -0.0353 0.7524 0.6579
-1.500 -0.0151 0.01697 0.00840 -0.0349 0.7470 0.6643
-1.250 0.0117 0.01694 0.00832 -0.0350 0.7392 0.6724
-1.000 0.0387 0.01693 0.00830 -0.0346 0.7332 0.6777
-0.750 0.0657 0.01693 0.00826 -0.0345 0.7267 0.6850
-0.500 0.0926 0.01693 0.00824 -0.0344 0.7199 0.6915
-0.250 0.1200 0.01691 0.00819 -0.0340 0.7148 0.6977
0.000 0.1469 0.01694 0.00820 -0.0342 0.7073 0.7058
0.250 0.1735 0.01696 0.00825 -0.0337 0.7012 0.7113
0.500 0.2009 0.01697 0.00824 -0.0336 0.6959 0.7185
0.750 0.2273 0.01704 0.00833 -0.0334 0.6885 0.7254
1.000 0.2543 0.01705 0.00836 -0.0331 0.6831 0.7319
1.250 0.2815 0.01711 0.00843 -0.0332 0.6768 0.7400
1.500 0.3072 0.01719 0.00857 -0.0327 0.6702 0.7461
1.750 0.3351 0.01719 0.00856 -0.0326 0.6652 0.7540
2.000 0.3604 0.01732 0.00878 -0.0322 0.6579 0.7608
2.250 0.3870 0.01738 0.00887 -0.0319 0.6518 0.7685
2.500 0.4140 0.01742 0.00895 -0.0316 0.6462 0.7760
2.750 0.4388 0.01756 0.00918 -0.0311 0.6386 0.7836
3.000 0.4661 0.01758 0.00923 -0.0309 0.6330 0.7917
3.250 0.4906 0.01772 0.00948 -0.0303 0.6254 0.7994
3.500 0.5170 0.01778 0.00960 -0.0300 0.6187 0.8081
3.750 0.5424 0.01786 0.00976 -0.0293 0.6121 0.8160
4.000 0.5675 0.01797 0.00998 -0.0289 0.6040 0.8251
4.250 0.5934 0.01799 0.01005 -0.0282 0.5972 0.8336
4.500 0.6172 0.01808 0.01026 -0.0275 0.5874 0.8429
4.750 0.6416 0.01808 0.01036 -0.0266 0.5771 0.8529
5.000 0.6667 0.01798 0.01030 -0.0257 0.5665 0.8621
5.250 0.6893 0.01802 0.01047 -0.0246 0.5535 0.8732
5.500 0.7118 0.01801 0.01058 -0.0234 0.5402 0.8846
5.750 0.7343 0.01797 0.01063 -0.0222 0.5248 0.8964
6.000 0.7568 0.01791 0.01065 -0.0210 0.5068 0.9096
6.250 0.7800 0.01785 0.01062 -0.0199 0.4848 0.9244
6.500 0.8037 0.01788 0.01070 -0.0193 0.4549 0.9413
6.750 0.8309 0.01806 0.01086 -0.0196 0.4147 0.9613
7.000 0.8587 0.01847 0.01110 -0.0204 0.3603 1.0000
7.250 0.8722 0.01924 0.01155 -0.0189 0.3039 1.0000
7.500 0.8824 0.02034 0.01229 -0.0173 0.2477 1.0000
7.750 0.8911 0.02161 0.01323 -0.0156 0.1982 1.0000
8.000 0.8995 0.02289 0.01427 -0.0139 0.1602 1.0000
8.250 0.9067 0.02412 0.01533 -0.0120 0.1322 1.0000
8.500 0.9131 0.02540 0.01648 -0.0101 0.1120 1.0000
8.750 0.9205 0.02673 0.01772 -0.0085 0.0974 1.0000
9.250 0.9363 0.02950 0.02045 -0.0058 0.0795 1.0000
9.500 0.9435 0.03103 0.02195 -0.0046 0.0740 1.0000
9.750 0.9531 0.03244 0.02342 -0.0036 0.0687 1.0000
10.000 0.9599 0.03411 0.02505 -0.0027 0.0649 1.0000
10.250 0.9705 0.03556 0.02658 -0.0018 0.0612 1.0000
10.500 0.9806 0.03708 0.02814 -0.0011 0.0578 1.0000
10.750 0.9890 0.03877 0.02982 -0.0004 0.0552 1.0000
11.000 1.0007 0.04029 0.03144 0.0003 0.0524 1.0000
11.250 1.0122 0.04186 0.03308 0.0009 0.0499 1.0000
11.500 1.0223 0.04353 0.03477 0.0013 0.0477 1.0000
11.750 1.0333 0.04526 0.03649 0.0019 0.0458 1.0000
12.000 1.0458 0.04694 0.03834 0.0024 0.0438 1.0000
12.250 1.0566 0.04874 0.04027 0.0028 0.0419 1.0000
12.500 1.0664 0.05061 0.04219 0.0031 0.0404 1.0000
12.750 1.0773 0.05248 0.04405 0.0033 0.0391 1.0000
13.000 1.0890 0.05456 0.04626 0.0037 0.0381 1.0000
13.250 1.0976 0.05695 0.04888 0.0040 0.0371 1.0000
13.500 1.1041 0.05956 0.05170 0.0042 0.0362 1.0000
13.750 1.1079 0.06238 0.05473 0.0041 0.0353 1.0000
14.000 1.1098 0.06533 0.05786 0.0038 0.0345 1.0000
14.250 1.1106 0.06840 0.06107 0.0034 0.0338 1.0000
14.500 1.1111 0.07151 0.06429 0.0028 0.0331 1.0000
14.750 1.1126 0.07461 0.06747 0.0021 0.0325 1.0000
15.000 1.1079 0.07864 0.07166 0.0010 0.0320 1.0000
15.250 1.0943 0.08389 0.07720 -0.0010 0.0317 1.0000
15.500 1.0776 0.08990 0.08351 -0.0036 0.0315 1.0000
15.750 1.0602 0.09640 0.09027 -0.0068 0.0314 1.0000
16.000 1.0382 0.10409 0.09823 -0.0111 0.0313 1.0000
16.250 1.0133 0.11293 0.10732 -0.0165 0.0313 1.0000
16.500 0.9840 0.12350 0.11813 -0.0233 0.0315 1.0000
16.750 0.9463 0.13732 0.13216 -0.0324 0.0318 1.0000
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