NACA 4424 (naca4424-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4424 (naca4424-il) Reynolds number: 100,000 Max Cl/Cd: 30.84 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4424-il-100000.txt Download as CSV file: xf-naca4424-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4424
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.8389 0.06440 0.05774 -0.0701 0.9748 0.1761
-11.500 -0.9128 0.05996 0.05287 -0.0631 0.9644 0.1766
-11.250 -0.9638 0.05666 0.04912 -0.0554 0.9529 0.1776
-11.000 -0.8570 0.05838 0.05137 -0.0655 0.9508 0.1830
-10.750 -0.8728 0.05674 0.04959 -0.0609 0.9397 0.1851
-10.500 -0.8907 0.05448 0.04705 -0.0565 0.9303 0.1878
-10.250 -0.9128 0.05194 0.04405 -0.0512 0.9208 0.1906
-10.000 -0.8997 0.05082 0.04291 -0.0498 0.9124 0.1937
-9.750 -0.8692 0.05054 0.04273 -0.0505 0.9047 0.1974
-9.500 -0.8425 0.04938 0.04141 -0.0514 0.8996 0.2025
-9.250 -0.8646 0.04810 0.03984 -0.0442 0.8871 0.2051
-9.000 -0.8318 0.04710 0.03884 -0.0456 0.8814 0.2095
-8.750 -0.8123 0.04676 0.03854 -0.0445 0.8731 0.2134
-8.500 -0.8026 0.04601 0.03767 -0.0420 0.8639 0.2177
-8.250 -0.7830 0.04459 0.03590 -0.0412 0.8587 0.2234
-8.000 -0.7735 0.04438 0.03582 -0.0384 0.8480 0.2265
-7.750 -0.7464 0.04395 0.03541 -0.0383 0.8409 0.2319
-7.500 -0.7199 0.04286 0.03397 -0.0382 0.8364 0.2388
-7.250 -0.7252 0.04263 0.03378 -0.0332 0.8244 0.2417
-7.000 -0.6897 0.04224 0.03351 -0.0344 0.8186 0.2474
-6.750 -0.6558 0.04142 0.03247 -0.0352 0.8148 0.2554
-6.500 -0.6699 0.04132 0.03224 -0.0286 0.8015 0.2585
-6.250 -0.6293 0.04083 0.03194 -0.0306 0.7967 0.2650
-6.000 -0.5934 0.04013 0.03109 -0.0315 0.7934 0.2737
-5.750 -0.6126 0.04042 0.03118 -0.0242 0.7796 0.2768
-5.500 -0.5707 0.03974 0.03072 -0.0263 0.7752 0.2841
-5.250 -0.5324 0.03906 0.02992 -0.0275 0.7722 0.2937
-5.000 -0.5545 0.03970 0.03040 -0.0199 0.7583 0.2968
-4.750 -0.5158 0.03903 0.02991 -0.0215 0.7540 0.3046
-4.500 -0.4759 0.03833 0.02912 -0.0227 0.7511 0.3149
-4.250 -0.4985 0.03921 0.02985 -0.0153 0.7372 0.3184
-4.000 -0.4628 0.03862 0.02944 -0.0163 0.7328 0.3268
-3.750 -0.4247 0.03798 0.02872 -0.0172 0.7299 0.3380
-3.500 -0.4465 0.03905 0.02966 -0.0102 0.7168 0.3416
-3.250 -0.4130 0.03854 0.02934 -0.0108 0.7118 0.3510
-3.000 -0.3773 0.03795 0.02862 -0.0112 0.7087 0.3632
-2.750 -0.3895 0.03892 0.02962 -0.0059 0.6975 0.3679
-2.500 -0.3673 0.03883 0.02963 -0.0049 0.6910 0.3774
-2.250 -0.3339 0.03828 0.02898 -0.0050 0.6875 0.3904
-2.000 -0.2881 0.03739 0.02823 -0.0070 0.6855 0.4045
-1.750 -0.3259 0.03953 0.03034 0.0014 0.6708 0.4071
-1.500 -0.2942 0.03908 0.02994 0.0013 0.6667 0.4204
-1.250 -0.2544 0.03837 0.02920 0.0004 0.6641 0.4371
-1.000 -0.2828 0.04034 0.03123 0.0071 0.6510 0.4412
-0.750 -0.2576 0.04025 0.03125 0.0078 0.6460 0.4557
-0.500 -0.2206 0.03965 0.03074 0.0072 0.6431 0.4734
-0.250 -0.1761 0.03872 0.02989 0.0059 0.6411 0.4948
0.000 -0.1297 0.03768 0.02895 0.0044 0.6398 0.5189
0.250 -0.1905 0.04134 0.03265 0.0142 0.6222 0.5191
0.500 -0.1502 0.04060 0.03204 0.0135 0.6199 0.5454
0.750 -0.1035 0.03952 0.03113 0.0122 0.6185 0.5765
1.000 -0.1607 0.04333 0.03500 0.0208 0.6018 0.5800
1.250 -0.1246 0.04280 0.03462 0.0206 0.5990 0.6169
1.500 -0.0746 0.04171 0.03381 0.0189 0.5973 0.6628
1.750 -0.0152 0.04050 0.03290 0.0156 0.5962 0.7224
2.250 0.2251 0.03713 0.03007 -0.0115 0.5960 0.8689
2.500 0.3643 0.03547 0.02834 -0.0278 0.5964 0.9003
2.750 0.4958 0.03381 0.02650 -0.0425 0.5961 0.9155
3.000 0.4305 0.03967 0.03260 -0.0337 0.5771 0.9409
3.250 0.5478 0.03746 0.03022 -0.0455 0.5772 0.9531
3.500 0.6744 0.03527 0.02783 -0.0596 0.5765 0.9624
3.750 0.6184 0.04105 0.03386 -0.0531 0.5591 0.9874
4.000 0.7511 0.03779 0.03041 -0.0673 0.5592 0.9929
4.250 0.8913 0.03512 0.02750 -0.0843 0.5567 0.9956
4.500 1.0338 0.03352 0.02560 -0.1035 0.5526 0.9966
4.750 0.5770 0.04711 0.03971 -0.0388 0.5287 1.0000
5.000 0.6462 0.04404 0.03651 -0.0419 0.5292 1.0000
5.250 0.7373 0.04061 0.03293 -0.0483 0.5296 1.0000
5.500 0.5761 0.05084 0.04326 -0.0296 0.5088 1.0000
5.750 0.6405 0.04775 0.04005 -0.0317 0.5092 1.0000
6.000 0.7175 0.04440 0.03658 -0.0355 0.5095 1.0000
6.500 0.4011 0.07291 0.06536 -0.0128 0.4561 1.0000
6.750 0.4286 0.07270 0.06510 -0.0121 0.4522 1.0000
7.000 0.4672 0.07150 0.06383 -0.0117 0.4500 1.0000
7.250 0.4140 0.07865 0.07103 -0.0090 0.4361 1.0000
7.500 0.4408 0.07856 0.07089 -0.0083 0.4321 1.0000
7.750 0.4808 0.07720 0.06947 -0.0078 0.4299 1.0000
8.000 0.4297 0.08453 0.07685 -0.0058 0.4162 1.0000
8.250 0.4568 0.08445 0.07673 -0.0051 0.4125 1.0000
8.500 0.4990 0.08278 0.07500 -0.0046 0.4102 1.0000
8.750 0.5435 0.08084 0.07301 -0.0041 0.4088 1.0000
9.000 0.4756 0.09036 0.08261 -0.0026 0.3931 1.0000
9.250 0.5152 0.08899 0.08118 -0.0020 0.3910 1.0000
9.500 0.5602 0.08690 0.07904 -0.0014 0.3896 1.0000
9.750 0.4922 0.09688 0.08911 -0.0007 0.3742 1.0000
10.000 0.5337 0.09518 0.08736 0.0001 0.3722 1.0000
10.250 0.4743 0.10465 0.09692 0.0001 0.3593 1.0000
10.500 0.5074 0.10384 0.09608 0.0008 0.3558 1.0000
10.750 0.4893 0.10898 0.10124 0.0008 0.3479 1.0000
11.000 0.4864 0.11232 0.10460 0.0009 0.3414 1.0000
11.250 0.5178 0.11172 0.10398 0.0016 0.3380 1.0000
11.500 0.5651 0.10908 0.10128 0.0027 0.3359 1.0000
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Polar data table (+)
Polar graphs
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