NACA 65(4)-221 (naca654221-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(4)-221 (naca654221-il) Reynolds number: 100,000 Max Cl/Cd: 20.74 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca654221-il-100000-n5.txt Download as CSV file: xf-naca654221-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(4)-221
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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6322 0.12369 0.11783 -0.0535 1.0000 0.0413
-17.500 -0.7124 0.10438 0.09810 -0.0647 1.0000 0.0404
-17.250 -0.7471 0.09542 0.08887 -0.0693 1.0000 0.0403
-17.000 -0.7702 0.08886 0.08207 -0.0723 1.0000 0.0404
-16.750 -0.7873 0.08348 0.07646 -0.0744 1.0000 0.0405
-16.500 -0.8003 0.07892 0.07169 -0.0759 1.0000 0.0408
-16.250 -0.8100 0.07486 0.06743 -0.0769 1.0000 0.0411
-16.000 -0.8174 0.07120 0.06357 -0.0777 1.0000 0.0414
-15.750 -0.8217 0.06794 0.06009 -0.0781 1.0000 0.0418
-15.500 -0.8240 0.06492 0.05686 -0.0784 1.0000 0.0423
-15.250 -0.8219 0.06231 0.05405 -0.0785 1.0000 0.0426
-15.000 -0.8170 0.05997 0.05150 -0.0784 1.0000 0.0430
-14.750 -0.8085 0.05792 0.04928 -0.0783 1.0000 0.0434
-14.500 -0.7902 0.05659 0.04795 -0.0782 1.0000 0.0439
-14.250 -0.7736 0.05530 0.04666 -0.0780 1.0000 0.0445
-14.000 -0.7584 0.05402 0.04537 -0.0778 1.0000 0.0452
-13.750 -0.7430 0.05285 0.04416 -0.0776 1.0000 0.0458
-13.500 -0.7284 0.05174 0.04302 -0.0772 1.0000 0.0467
-13.250 -0.7152 0.05074 0.04198 -0.0766 1.0000 0.0477
-13.000 -0.6894 0.04943 0.04054 -0.0783 0.9754 0.0492
-12.750 -0.6614 0.04833 0.03943 -0.0802 0.9617 0.0507
-12.500 -0.6351 0.04712 0.03820 -0.0822 0.9498 0.0522
-12.250 -0.6098 0.04597 0.03699 -0.0839 0.9385 0.0539
-12.000 -0.5864 0.04486 0.03576 -0.0851 0.9276 0.0557
-11.750 -0.5687 0.04374 0.03458 -0.0855 0.9158 0.0575
-11.500 -0.5544 0.04253 0.03334 -0.0856 0.9048 0.0596
-11.250 -0.5405 0.04142 0.03214 -0.0854 0.8949 0.0626
-11.000 -0.5292 0.04033 0.03100 -0.0847 0.8844 0.0657
-10.750 -0.5187 0.03918 0.02981 -0.0840 0.8759 0.0699
-10.500 -0.5087 0.03810 0.02870 -0.0831 0.8664 0.0748
-10.250 -0.4998 0.03696 0.02754 -0.0820 0.8591 0.0824
-10.000 -0.4922 0.03578 0.02644 -0.0808 0.8509 0.0942
-9.750 -0.4863 0.03453 0.02532 -0.0795 0.8437 0.1133
-9.500 -0.4838 0.03312 0.02410 -0.0779 0.8370 0.1458
-9.250 -0.4830 0.03167 0.02286 -0.0762 0.8293 0.1812
-9.000 -0.4859 0.03009 0.02148 -0.0739 0.8229 0.2211
-8.500 -0.4948 0.02717 0.01911 -0.0687 0.8090 0.3148
-8.250 -0.4864 0.02681 0.01920 -0.0660 0.8041 0.3803
-8.000 -0.4473 0.02855 0.02123 -0.0652 0.7999 0.4403
-7.750 -0.4346 0.02852 0.02121 -0.0634 0.7937 0.4736
-7.500 -0.4353 0.02771 0.02033 -0.0606 0.7880 0.5002
-7.250 -0.4289 0.02765 0.02018 -0.0577 0.7836 0.5231
-7.000 -0.4124 0.02841 0.02091 -0.0555 0.7777 0.5409
-6.750 -0.4200 0.02783 0.02025 -0.0512 0.7717 0.5557
-6.500 -0.3638 0.02973 0.02201 -0.0532 0.7690 0.5601
-6.250 -0.3811 0.02855 0.02073 -0.0479 0.7649 0.5734
-5.750 -0.3495 0.02892 0.02094 -0.0444 0.7552 0.5903
-5.500 -0.3047 0.02994 0.02186 -0.0457 0.7519 0.5927
-5.000 -0.2828 0.02913 0.02080 -0.0416 0.7453 0.6083
-4.750 -0.2512 0.02962 0.02125 -0.0419 0.7411 0.6105
-4.250 -0.2403 0.02845 0.01991 -0.0370 0.7328 0.6255
-4.000 -0.2083 0.02862 0.01999 -0.0374 0.7302 0.6272
-3.750 -0.1781 0.02868 0.01996 -0.0377 0.7279 0.6294
-3.500 -0.1559 0.02876 0.02000 -0.0370 0.7240 0.6325
-3.250 -0.1686 0.02767 0.01884 -0.0327 0.7187 0.6429
-3.000 -0.1429 0.02772 0.01885 -0.0325 0.7156 0.6450
-2.750 -0.1161 0.02775 0.01882 -0.0325 0.7131 0.6469
-2.500 -0.0904 0.02767 0.01867 -0.0323 0.7109 0.6493
-2.250 -0.0664 0.02747 0.01839 -0.0320 0.7089 0.6526
-2.000 -0.0647 0.02716 0.01807 -0.0292 0.7035 0.6588
-1.750 -0.0530 0.02689 0.01776 -0.0276 0.6992 0.6630
-1.500 -0.0284 0.02698 0.01783 -0.0272 0.6964 0.6650
-1.250 -0.0032 0.02698 0.01780 -0.0270 0.6941 0.6673
-1.000 0.0215 0.02686 0.01763 -0.0269 0.6922 0.6700
-0.750 0.0457 0.02662 0.01732 -0.0268 0.6905 0.6733
-0.500 0.0435 0.02671 0.01741 -0.0236 0.6842 0.6794
-0.250 0.0611 0.02687 0.01758 -0.0224 0.6802 0.6820
0.000 0.0845 0.02698 0.01770 -0.0219 0.6775 0.6840
0.250 0.1095 0.02699 0.01771 -0.0218 0.6754 0.6862
0.500 0.1358 0.02693 0.01763 -0.0219 0.6737 0.6888
0.750 0.1634 0.02680 0.01746 -0.0222 0.6722 0.6920
1.000 0.1503 0.02765 0.01837 -0.0175 0.6635 0.6976
1.250 0.1688 0.02783 0.01856 -0.0166 0.6602 0.7005
1.500 0.1929 0.02798 0.01873 -0.0163 0.6580 0.7026
1.750 0.2200 0.02800 0.01877 -0.0164 0.6563 0.7049
2.000 0.2497 0.02793 0.01871 -0.0169 0.6548 0.7075
2.500 0.2439 0.02974 0.02059 -0.0101 0.6413 0.7163
2.750 0.2710 0.02974 0.02061 -0.0104 0.6393 0.7195
3.000 0.3008 0.02971 0.02064 -0.0107 0.6378 0.7218
3.250 0.3320 0.02965 0.02062 -0.0114 0.6365 0.7243
3.750 0.3162 0.03209 0.02315 -0.0035 0.6209 0.7323
4.000 0.3029 0.03413 0.02522 -0.0002 0.6105 0.7375
4.250 0.3222 0.03452 0.02569 0.0007 0.6065 0.7402
4.500 0.3495 0.03452 0.02576 0.0007 0.6042 0.7433
4.750 0.3797 0.03436 0.02567 0.0004 0.6025 0.7468
5.000 0.4124 0.03408 0.02544 -0.0002 0.6013 0.7506
5.750 0.4355 0.03717 0.02875 0.0045 0.5802 0.7625
6.250 0.4715 0.03804 0.02978 0.0059 0.5689 0.7718
7.250 0.5533 0.03875 0.03088 0.0085 0.5469 0.7900
7.750 0.5954 0.03866 0.03101 0.0101 0.5338 0.8000
8.250 0.6296 0.03906 0.03163 0.0120 0.5176 0.8121
9.250 0.6825 0.04049 0.03354 0.0172 0.4746 0.8370
9.750 0.7164 0.03993 0.03312 0.0199 0.4360 0.8528
10.000 0.7341 0.03950 0.03268 0.0215 0.4043 0.8613
10.250 0.7670 0.03784 0.03081 0.0226 0.3620 0.8700
10.500 0.7831 0.03776 0.03045 0.0244 0.3196 0.8794
10.750 0.7861 0.03897 0.03145 0.0262 0.2800 0.8898
11.000 0.7857 0.04067 0.03296 0.0279 0.2448 0.9023
11.250 0.7846 0.04261 0.03474 0.0292 0.2107 0.9172
11.500 0.7864 0.04471 0.03670 0.0297 0.1775 0.9348
11.750 0.7918 0.04702 0.03885 0.0289 0.1434 0.9574
12.000 0.7943 0.04910 0.04075 0.0288 0.1145 1.0000
12.250 0.7992 0.05129 0.04275 0.0287 0.0926 1.0000
12.500 0.8052 0.05343 0.04476 0.0286 0.0789 1.0000
12.750 0.8123 0.05551 0.04678 0.0284 0.0702 1.0000
13.000 0.8199 0.05757 0.04881 0.0283 0.0645 1.0000
13.250 0.8268 0.05970 0.05092 0.0281 0.0603 1.0000
13.500 0.8354 0.06168 0.05294 0.0279 0.0570 1.0000
13.750 0.8434 0.06374 0.05501 0.0276 0.0541 1.0000
14.000 0.8508 0.06588 0.05713 0.0274 0.0517 1.0000
14.250 0.8606 0.06777 0.05909 0.0272 0.0497 1.0000
14.500 0.8702 0.06966 0.06103 0.0270 0.0481 1.0000
14.750 0.8795 0.07159 0.06295 0.0267 0.0467 1.0000
15.000 0.8904 0.07331 0.06465 0.0266 0.0456 1.0000
15.250 0.9030 0.07493 0.06637 0.0265 0.0442 1.0000
15.500 0.9151 0.07660 0.06811 0.0263 0.0429 1.0000
15.750 0.9271 0.07830 0.06986 0.0261 0.0419 1.0000
16.000 0.9374 0.08019 0.07173 0.0257 0.0406 1.0000
16.250 0.9517 0.08159 0.07310 0.0256 0.0398 1.0000
16.500 0.9628 0.08355 0.07522 0.0253 0.0389 1.0000
16.750 0.9742 0.08549 0.07730 0.0250 0.0382 1.0000
17.000 0.9845 0.08758 0.07951 0.0246 0.0376 1.0000
17.250 0.9932 0.08990 0.08196 0.0241 0.0370 1.0000
17.500 1.0009 0.09236 0.08453 0.0235 0.0365 1.0000
17.750 1.0074 0.09500 0.08729 0.0227 0.0360 1.0000
18.000 1.0130 0.09774 0.09013 0.0219 0.0356 1.0000
18.250 1.0188 0.10045 0.09292 0.0209 0.0351 1.0000
18.500 1.0271 0.10285 0.09536 0.0202 0.0346 1.0000
18.750 1.0200 0.10751 0.10025 0.0183 0.0344 1.0000
19.000 1.0098 0.11273 0.10574 0.0159 0.0341 1.0000
19.250 0.9951 0.11884 0.11212 0.0129 0.0338 1.0000
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